From 2a91994cf6f19dd7c222f308ba36b2887a9eb0f1 Mon Sep 17 00:00:00 2001 From: m-selig Date: Sat, 5 Oct 2024 20:48:05 -0500 Subject: [PATCH] - Increased version number for 4.2g for better tracking with another repo. - Added additional iteration types for Alpha*. - Changed "STATISTICS" output ordering. - Updated some code references (comments). - Updated ./src/test/results-gfortran files/ --- src/PROFOIL.INC | 3 +- src/alfainc.f | 28 + src/coord.f | 5 +- src/deflt.f | 4 + src/echo.f | 2 +- src/norm.f | 2 + src/probl.f | 4 + src/profoil.f | 10 +- src/setnew.f | 28 + src/stats.f | 26 +- src/stoptst.f | 10 +- .../results-gfortran/profoil_test_long.txt | 1365 +++++++++++++++-- .../results-gfortran/profoil_test_short.txt | 186 ++- .../results-gfortran/profoil_test_tra.txt | 4 +- 14 files changed, 1508 insertions(+), 169 deletions(-) diff --git a/src/PROFOIL.INC b/src/PROFOIL.INC index ff9b699..48dd57c 100644 --- a/src/PROFOIL.INC +++ b/src/PROFOIL.INC @@ -289,7 +289,7 @@ C-----setup for call to BL subroutine $ TMAP(NARGP), $ AX(NARGP), BX(NARGP), CX(NARGP), DX(NARGP), $ AY(NARGP), BY(NARGP), CY(NARGP), DY(NARGP), - $ SX + $ SX, $ SY COMMON/ NRM/ $ XLE(4), @@ -299,6 +299,7 @@ C-----setup for call to BL subroutine $ XTMP(NARGP), $ YTMP(NARGP), $ ALFA0, + $ ALFA0_BUMP, $ CHORD, $ IMAX, $ INORMMETHOD diff --git a/src/alfainc.f b/src/alfainc.f index c3b451a..b2d1947 100644 --- a/src/alfainc.f +++ b/src/alfainc.f @@ -37,6 +37,34 @@ SUBROUTINE ALFAINC(ICASE, DELTA) DO I = ILE+1, ISEG ALFAS(I) = ALFAS(I) + DELTA ENDDO + ELSEIF (ICASE .EQ. 500) THEN + DO I = 1, ILE + ALFAS(I) = ALFAS(I) + DELTA + ENDDO + ALFAS(1) = ALFAS(1) - DELTA + ELSEIF (ICASE .EQ. 600) THEN + DO I = ILE+1, ISEG + ALFAS(I) = ALFAS(I) + DELTA + ENDDO + ALFAS(ISEG) = ALFAS(ISEG) - DELTA + ELSEIF (ICASE .EQ. 700) THEN + DO I = 1, ILE + ALFAS(I) = ALFAS(I) + DELTA + ENDDO + ALFAS(1) = ALFAS(1) - DELTA + DO I = ILE+1, ISEG + ALFAS(I) = ALFAS(I) - DELTA + ENDDO + ALFAS(ISEG) = ALFAS(ISEG) + DELTA + ELSEIF (ICASE .EQ. 800) THEN + DO I = 1, ILE + ALFAS(I) = ALFAS(I) + DELTA + ENDDO + ALFAS(1) = ALFAS(1) - DELTA + DO I = ILE+1, ISEG + ALFAS(I) = ALFAS(I) + DELTA + ENDDO + ALFAS(ISEG) = ALFAS(ISEG) - DELTA ELSE WRITE(LU06,*) ' WARNING: BUMPALFAS case not found (alfainc.f)' ENDIF diff --git a/src/coord.f b/src/coord.f index aa4fe92..ec4452c 100644 --- a/src/coord.f +++ b/src/coord.f @@ -42,8 +42,9 @@ SUBROUTINE COORD ENDIF FACTOR = 0.041666666666666666*DEL_PHI*DTOR IF (LTEZERO) THEN -C... Trailing edge is closed. -C... Otherwise TEY and/or TEX are specified by NEWT1* line +C... Trailing edge is closed, LTEZERO=TT. +C... Otherwise with LTEZERO=FF, then TEY, TEX, ... are specified by NEWT1G0 line(s) +C... with Newton iteration types: 155, 156, 157, and 158. DELSX = SX/FLOAT(IARGP-1) DELSY = SY/FLOAT(IARGP-1) ENDIF diff --git a/src/deflt.f b/src/deflt.f index 65e96c1..4793488 100644 --- a/src/deflt.f +++ b/src/deflt.f @@ -77,6 +77,10 @@ SUBROUTINE DEFLT C INORMMETHOD = 1 ... Legacy 3-pt parabola. Default. C INORMMETHOD = 2 ... Cubic spline. Recommended setting. INORMMETHOD = 1 +C---- Offset calculation of ALFA0 in norm.f +C Used to make closer match to Eppler airfoil coordinates when +C converting Eppler TRA data to PROFOIL data + ALFA0_BUMP = 0.0 C---- no trailing edge thickness wedge LWEDGE = FF C---- flip airfoil over diff --git a/src/echo.f b/src/echo.f index a206fc8..f072fb0 100644 --- a/src/echo.f +++ b/src/echo.f @@ -14,7 +14,7 @@ SUBROUTINE ECHO(ICASE) IF (ICASE .EQ. 0) THEN OPEN (UNIT=LU85,FILE=FILE85,STATUS='unknown') WRITE(LU85,1000) - 1000 FORMAT(//8X,'PROFOIL Version 2.0 March 2022' // + 1000 FORMAT(//8X,'PROFOIL Version 4.2g October 2024' // & 2X,'ITERATION 0'/) ELSE OPEN (UNIT=LU85,FILE=FILE85,STATUS='OLD',ACCESS='APPEND') diff --git a/src/norm.f b/src/norm.f index c1e4d39..fc77f6f 100644 --- a/src/norm.f +++ b/src/norm.f @@ -59,6 +59,7 @@ SUBROUTINE NORM YLE(4) = - XMAX * DSING(-THETA) + YMAX * DCOSG(-THETA) C-------rotate airfoil from zero lift angle of attack ALFA0 ALFA0 = DATAN(YLE(4)/XLE(4)) * RTOD + ALFA0 = ALFA0 + ALFA0_BUMP CHORD = DSQRT(XLE(4)**2 + YLE(4)**2) ELSEIF (INORMMETHOD .EQ. 2) THEN C-------Use a cubic spline (natural cubic spline / second derivative is zero at the endpoints) @@ -108,6 +109,7 @@ SUBROUTINE NORM C-------rotate airfoil from zero lift angle of attack ALFA0 ALFA0 = DATAN(RMAXY/RMAXX) * RTOD + ALFA0 = ALFA0 + ALFA0_BUMP CHORD = DSQRT(RMAXX**2 + RMAXY**2) ENDIF diff --git a/src/probl.f b/src/probl.f index 73f21f4..2353d0c 100644 --- a/src/probl.f +++ b/src/probl.f @@ -47,6 +47,10 @@ SUBROUTINE PROBL C Eppler, Richard, "Practical Calculations of Laminar and Turbulent C Bled-Off Boundary Layers," NASA TM-75328, Sept 1978 C https://ntrs.nasa.gov/citations/19780024110 +C Boundary Layer integration tests are also included in: +C Miley, Stanley, "An Analysis of the Design of Airfoil Sections +C for Low Reynolds Numbers," PhD Dissertation, Mississippi State Univ, +C January 1972, p169-170. C C Copyright (c) 1990-2022 Michael Selig C*********************************************************************** diff --git a/src/profoil.f b/src/profoil.f index fe1e2ff..866f8c9 100644 --- a/src/profoil.f +++ b/src/profoil.f @@ -2,7 +2,7 @@ PROGRAM PROFOIL C********************************************************************** -C PROFOIL Version 2.1 September 2024 +C PROFOIL Version 4.2g October 2024 / MIT License" C Multi-Point Inverse Airfoil Design C Copyright (c) 1990-2024 Michael Selig C Copyright (c) 1995 Ashok Gopalarathnam @@ -22,7 +22,8 @@ PROGRAM PROFOIL 1005 FORMAT(2X,' Airfoil/Comment: ',A) C---- Write current version number to a file OPEN (UNIT = 61, FILE = 'version.txt', status='unknown') - WRITE(61,*) "PROFOIL v2.1 September 2024 / MIT License" + WRITE(61,*) "PROFOIL v4.2g October 2024 / MIT License" + C-----set the constants CALL SETUP C-----set the default values @@ -56,8 +57,10 @@ PROGRAM PROFOIL call stoptst ELSEIF (LINE(1:1) .EQ. ' ') THEN C--- skip this line +C--------******************************************** ELSEIF (LINE(1:1) .EQ. '*') THEN C--- finished reading in data from input file unit LU10 + WRITE(LU06,*) "PROFOIL v4.2g October 2024 / MIT License" CLOSE(LU10) LEND = TT C--------AAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAAA @@ -76,6 +79,9 @@ PROGRAM PROFOIL WRITE(LU06,1005) LINE(9:50) WRITE(LU06,*) ' ********************************************' WRITE(LU06,*) + ELSEIF (LINE(1:10) .EQ. 'ALFA0_BUMP') THEN + WRITE(TLINE, 1000) LINE(11:50) + READ(TLINE,*) ALFA0_BUMP ELSEIF (LINE(1:6) .EQ. 'ALFASP') THEN WRITE(TLINE, 1000) LINE(7:50) READ(TLINE,*) IALF diff --git a/src/setnew.f b/src/setnew.f index 9f39b94..41cfd2c 100644 --- a/src/setnew.f +++ b/src/setnew.f @@ -224,6 +224,34 @@ SUBROUTINE SETNEW(JVAR1,ISIGN1,ISIGN2) DO 242 I = ILE+1, ISEG ALFAS(I) = ALFAS(I) + DELTAJ 242 CONTINUE + ELSEIF (ICASE .EQ. 5) THEN + DO 212 I = 1, ILE + ALFAS(I) = ALFAS(I) + DELTAJ + 212 CONTINUE + ALFAS(1) = ALFAS(1) - DELTAJ + ELSEIF (ICASE .EQ. 6) THEN + DO 222 I = ILE+1, ISEG + ALFAS(I) = ALFAS(I) + DELTAJ + 222 CONTINUE + ALFAS(ISEG) = ALFAS(ISEG) - DELTAJ + ELSEIF (ICASE .EQ. 7) THEN + DO 233 I = 1, ILE + ALFAS(I) = ALFAS(I) + DELTAJ + 233 CONTINUE + ALFAS(1) = ALFAS(1) - DELTAJ + DO 234 I = ILE+1, ISEG + ALFAS(I) = ALFAS(I) - DELTAJ + 234 CONTINUE + ALFAS(ISEG) = ALFAS(ISEG) + DELTAJ + ELSEIF (ICASE .EQ. 8) THEN + DO 243 I = 1, ILE + ALFAS(I) = ALFAS(I) + DELTAJ + 243 CONTINUE + ALFAS(1) = ALFAS(1) - DELTAJ + DO 244 I = ILE+1, ISEG + ALFAS(I) = ALFAS(I) + DELTAJ + 244 CONTINUE + ALFAS(ISEG) = ALFAS(ISEG) - DELTAJ ELSE WRITE(LU06,*) 'Error 202: ICASE not found (setnew.f)' ENDIF diff --git a/src/stats.f b/src/stats.f index 83afc6a..397731b 100644 --- a/src/stats.f +++ b/src/stats.f @@ -12,25 +12,25 @@ SUBROUTINE STATS WRITE(lu06,*) 'Finished case:', JFOIL WRITE(lu06,*) '***************************' ENDIF - WRITE(lu06,1001) IARGP, CHORD, -ALFA0, CM0, 100.*THKMAX, + WRITE(lu06,1001) IARGP, -ALFA0, CM0, 100.*THKMAX, $ 100.*THKMAXE, $ 100.*CMBMAX, $ 100.*XCMAXE, - $ 100.*XCMAX, SX, SY, + $ 100.*XCMAX, CHORD, SX, SY, $ FSB0, FSA1, FSB1 WRITE(lu06,*) 1001 FORMAT(2X,' **** STATISTICS ****'/ - $ 2X,' IARGP = ', I10,/ - $ 2X,' CHORD = ',F10.3,/ - $ 2X,' ALFA0 = ',F10.3,/ - $ 2X,' CM0 = ',F10.4,/ - $ 2X,' THKMAX = ',F9.2,'%',/ - $ 2X,' THKMAXE= ',F9.2,'%',/ - $ 2X,' CMBMAX = ',F9.2,'%',/ - $ 2X,' XCMAX = ',F9.2,'%',/ - $ 2X,' XCMAXE = ',F9.2,'%',/ - $ 2X,' SX = ',F10.3,/ - $ 2X,' SY = ',F10.3,/ + $ 2X,' POINTS = ', I10,/ + $ 2X,' ALFA_0 = ',F10.3,/ + $ 2X,' CM_0 = ',F10.4,/ + $ 2X,' THKMAX = ',F9.3,'%',/ + $ 2X,' THKMAXE= ',F9.3,'%',/ + $ 2X,' CMBMAX = ',F9.3,'%',/ + $ 2X,' XCMAX = ',F9.3,'%',/ + $ 2X,' XCMAXE = ',F9.3,'%',/ + $ 2X,' CHORD = ',F5.3,'(MAP)'/ + $ 2X,' SX = ',F10.6,/ + $ 2X,' SY = ',F10.6,/ $ 2X,' B0 = ',F10.6,/ $ 2X,' A1 = ',F10.6,/ $ 2X,' B1 = ',F10.6,/ diff --git a/src/stoptst.f b/src/stoptst.f index e28a959..79e57b7 100644 --- a/src/stoptst.f +++ b/src/stoptst.f @@ -7,9 +7,13 @@ subroutine stoptst c*********************************************************************** include 'PROFOIL.INC' write(lu06,*) ' **************************************' - write(lu06,*) ' Do you wish to stop (1 = yes; 0 = no)?' - read(lu05,*) istop - if(istop .eq. 1) stop + +c... write(lu06,*) ' Do you wish to stop (1 = yes; 0 = no)?' +c... read(lu05,*) istop +c... if(istop .eq. 1) stop + +c... Simply stop and let user read the error message + stop return end ! stoptst diff --git a/src/test/results-gfortran/profoil_test_long.txt b/src/test/results-gfortran/profoil_test_long.txt index 642e24f..61909d6 100644 --- a/src/test/results-gfortran/profoil_test_long.txt +++ b/src/test/results-gfortran/profoil_test_long.txt @@ -1,4 +1,4 @@ -Thu Nov 24 21:56:45 CST 2022 +Sat Oct 5 20:30:01 CDT 2024 ************************************ Running file: test-1000-four-seg.in ************************************ @@ -112,19 +112,20 @@ Output from file: test-1000-four-seg.in Airfoil/Comment: Different comment - EXAMPLE1 Four Segment ******************************************** + PROFOIL v4.2g October 2024 / MIT License **** STATISTICS **** - IARGP = 60 - CHORD = 3.708 - ALFA0 = -5.559 - CM0 = -0.1500 - THKMAX = 11.21% - THKMAXE= 11.21% - CMBMAX = 3.60% - XCMAX = 38.91% - XCMAXE = 38.91% - SX = 0.013 - SY = -0.019 + POINTS = 60 + ALFA_0 = -5.559 + CM_0 = -0.1500 + THKMAX = 11.213% + THKMAXE= 11.213% + CMBMAX = 3.596% + XCMAX = 38.910% + XCMAXE = 38.910% + CHORD = 3.708(MAP) + SX = 0.013009 + SY = -0.019065 B0 = 0.004643 A1 = 1.000253 B1 = -0.004694 @@ -501,19 +502,20 @@ Output from file: test-1005-thin-symmetrical.in Airfoil/Comment: test-1005-thin-symmetrical ******************************************** + PROFOIL v4.2g October 2024 / MIT License **** STATISTICS **** - IARGP = 60 - CHORD = 3.756 - ALFA0 = 0.000 - CM0 = 0.0000 - THKMAX = 8.00% - THKMAXE= 8.00% - CMBMAX = 0.00% - XCMAX = 18.38% - XCMAXE = 18.38% - SX = -0.000 - SY = 0.007 + POINTS = 60 + ALFA_0 = 0.000 + CM_0 = 0.0000 + THKMAX = 8.000% + THKMAXE= 8.000% + CMBMAX = 0.000% + XCMAX = 18.383% + XCMAXE = 18.383% + CHORD = 3.756(MAP) + SX = -0.000000 + SY = 0.006910 B0 = -0.000000 A1 = 0.999948 B1 = -0.000000 @@ -982,19 +984,20 @@ Output from file: test-1010-delv.in Airfoil/Comment: DELV Example ******************************************** + PROFOIL v4.2g October 2024 / MIT License **** STATISTICS **** - IARGP = 180 - CHORD = 3.617 - ALFA0 = -5.410 - CM0 = -0.1800 - THKMAX = 15.00% - THKMAXE= 15.00% - CMBMAX = 2.71% - XCMAX = 32.80% - XCMAXE = 32.80% - SX = 0.008 - SY = 0.006 + POINTS = 180 + ALFA_0 = -5.410 + CM_0 = -0.1800 + THKMAX = 15.000% + THKMAXE= 15.000% + CMBMAX = 2.714% + XCMAX = 32.803% + XCMAXE = 32.803% + CHORD = 3.617(MAP) + SX = 0.008255 + SY = 0.005573 B0 = 0.000201 A1 = 1.000017 B1 = -0.000200 @@ -1400,19 +1403,20 @@ Output from file: test-1030-many-segments-and-tra.in Airfoil/Comment: test-1030 This airfoil has many segements ******************************************** + PROFOIL v4.2g October 2024 / MIT License **** STATISTICS **** - IARGP = 60 - CHORD = 3.654 - ALFA0 = -3.534 - CM0 = -0.0911 - THKMAX = 11.70% - THKMAXE= 11.70% - CMBMAX = 2.73% - XCMAX = 37.64% - XCMAXE = 37.64% - SX = 0.009 - SY = -0.009 + POINTS = 60 + ALFA_0 = -3.534 + CM_0 = -0.0911 + THKMAX = 11.701% + THKMAXE= 11.701% + CMBMAX = 2.726% + XCMAX = 37.637% + XCMAXE = 37.637% + CHORD = 3.654(MAP) + SX = 0.008626 + SY = -0.009200 B0 = 0.001345 A1 = 1.000209 B1 = -0.001224 @@ -1950,19 +1954,20 @@ Output from file: test-1035-high-lift.in Airfoil/Comment: High Lift ******************************************** + PROFOIL v4.2g October 2024 / MIT License **** STATISTICS **** - IARGP = 60 - CHORD = 3.592 - ALFA0 = -13.862 - CM0 = -0.3500 - THKMAX = 10.80% - THKMAXE= 10.80% - CMBMAX = 11.41% - XCMAX = 25.34% - XCMAXE = 25.34% - SX = -0.002 - SY = 0.000 + POINTS = 60 + ALFA_0 = -13.862 + CM_0 = -0.3500 + THKMAX = 10.798% + THKMAXE= 10.798% + CMBMAX = 11.411% + XCMAX = 25.341% + XCMAXE = 25.341% + CHORD = 3.592(MAP) + SX = -0.001930 + SY = 0.000244 B0 = -0.001007 A1 = 0.999384 B1 = 0.000944 @@ -2422,19 +2427,20 @@ Output from file: test-1040-wind-turbine-root.in Airfoil/Comment: WindTurbineRoot ******************************************** + PROFOIL v4.2g October 2024 / MIT License **** STATISTICS **** - IARGP = 60 - CHORD = 3.370 - ALFA0 = -3.356 - CM0 = -0.1406 - THKMAX = 27.00% - THKMAXE= 27.00% - CMBMAX = 2.09% - XCMAX = 30.05% - XCMAXE = 30.05% - SX = 0.012 - SY = 0.005 + POINTS = 60 + ALFA_0 = -3.356 + CM_0 = -0.1406 + THKMAX = 27.000% + THKMAXE= 27.000% + CMBMAX = 2.092% + XCMAX = 30.047% + XCMAXE = 30.047% + CHORD = 3.370(MAP) + SX = 0.012499 + SY = 0.004963 B0 = 0.001095 A1 = 1.000071 B1 = -0.000925 @@ -2849,19 +2855,20 @@ Output from file: test-1050-sun.in *** --> profoil.dmp *** ************************* + PROFOIL v4.2g October 2024 / MIT License **** STATISTICS **** - IARGP = 60 - CHORD = 3.616 - ALFA0 = 0.000 - CM0 = 0.0000 - THKMAX = 13.20% - THKMAXE= 13.20% - CMBMAX = 0.00% - XCMAX = 43.12% - XCMAXE = 43.12% - SX = -0.000 - SY = 0.010 + POINTS = 60 + ALFA_0 = 0.000 + CM_0 = 0.0000 + THKMAX = 13.200% + THKMAXE= 13.200% + CMBMAX = 0.000% + XCMAX = 43.124% + XCMAXE = 43.124% + CHORD = 3.616(MAP) + SX = -0.000000 + SY = 0.009789 B0 = -0.000000 A1 = 0.999932 B1 = -0.000000 @@ -3165,19 +3172,20 @@ Output from file: test-1055.in Airfoil/Comment: test-1055 ******************************************** + PROFOIL v4.2g October 2024 / MIT License **** STATISTICS **** - IARGP = 60 - CHORD = 3.509 - ALFA0 = -5.603 - CM0 = -0.1400 - THKMAX = 18.22% - THKMAXE= 18.22% - CMBMAX = 3.89% - XCMAX = 35.12% - XCMAXE = 35.12% - SX = -0.005 - SY = -0.014 + POINTS = 60 + ALFA_0 = -5.603 + CM_0 = -0.1400 + THKMAX = 18.220% + THKMAXE= 18.220% + CMBMAX = 3.889% + XCMAX = 35.118% + XCMAXE = 35.118% + CHORD = 3.509(MAP) + SX = -0.004791 + SY = -0.013973 B0 = -0.001073 A1 = 0.999818 B1 = 0.001042 @@ -3510,19 +3518,20 @@ Output from file: test-1060.in Airfoil/Comment: test-1060 ******************************************** + PROFOIL v4.2g October 2024 / MIT License **** STATISTICS **** - IARGP = 120 - CHORD = 3.496 - ALFA0 = -6.350 - CM0 = -0.1400 - THKMAX = 18.22% - THKMAXE= 18.22% - CMBMAX = 5.72% - XCMAX = 32.28% - XCMAXE = 32.28% - SX = -0.008 - SY = -0.001 + POINTS = 120 + ALFA_0 = -6.350 + CM_0 = -0.1400 + THKMAX = 18.220% + THKMAXE= 18.220% + CMBMAX = 5.719% + XCMAX = 32.283% + XCMAXE = 32.283% + CHORD = 3.496(MAP) + SX = -0.007904 + SY = -0.001304 B0 = -0.000362 A1 = 0.999906 B1 = 0.000320 @@ -3886,19 +3895,20 @@ Output from file: test-1065-concave-recovery.in Airfoil/Comment: Low moment concave recovery ******************************************** + PROFOIL v4.2g October 2024 / MIT License **** STATISTICS **** - IARGP = 240 - CHORD = 3.556 - ALFA0 = -1.431 - CM0 = 0.0200 - THKMAX = 16.98% - THKMAXE= 16.98% - CMBMAX = 5.21% - XCMAX = 22.69% - XCMAXE = 22.69% - SX = -0.001 - SY = -0.002 + POINTS = 240 + ALFA_0 = -1.431 + CM_0 = 0.0200 + THKMAX = 16.981% + THKMAXE= 16.981% + CMBMAX = 5.211% + XCMAX = 22.690% + XCMAXE = 22.690% + CHORD = 3.556(MAP) + SX = -0.000670 + SY = -0.002238 B0 = 0.000038 A1 = 0.999998 B1 = -0.000029 @@ -4515,19 +4525,20 @@ Output from file: test-1075.in *** --> profoil.dmp *** ************************* + PROFOIL v4.2g October 2024 / MIT License **** STATISTICS **** - IARGP = 60 - CHORD = 3.652 - ALFA0 = -8.615 - CM0 = -0.2300 - THKMAX = 12.00% - THKMAXE= 12.00% - CMBMAX = 5.89% - XCMAX = 28.67% - XCMAXE = 28.67% - SX = -0.002 - SY = 0.000 + POINTS = 60 + ALFA_0 = -8.615 + CM_0 = -0.2300 + THKMAX = 12.000% + THKMAXE= 12.000% + CMBMAX = 5.895% + XCMAX = 28.675% + XCMAXE = 28.675% + CHORD = 3.652(MAP) + SX = -0.001882 + SY = 0.000300 B0 = -0.001388 A1 = 0.999731 B1 = 0.001391 @@ -4901,19 +4912,20 @@ Output from file: test-1080-reflex.in *** --> profoil.dmp *** ************************* + PROFOIL v4.2g October 2024 / MIT License **** STATISTICS **** - IARGP = 60 - CHORD = 3.734 - ALFA0 = 0.584 - CM0 = 0.0500 - THKMAX = 9.00% - THKMAXE= 9.00% - CMBMAX = 2.92% - XCMAX = 31.87% - XCMAXE = 31.87% - SX = 0.003 - SY = -0.009 + POINTS = 60 + ALFA_0 = 0.584 + CM_0 = 0.0500 + THKMAX = 9.000% + THKMAXE= 9.000% + CMBMAX = 2.916% + XCMAX = 31.865% + XCMAXE = 31.865% + CHORD = 3.734(MAP) + SX = 0.003171 + SY = -0.008940 B0 = 0.001575 A1 = 1.000123 B1 = -0.001517 @@ -5181,19 +5193,20 @@ Output from file: test-1093-like-7003.in Airfoil/Comment: SD7003-LIKE ******************************************** + PROFOIL v4.2g October 2024 / MIT License **** STATISTICS **** - IARGP = 60 - CHORD = 3.747 - ALFA0 = -1.878 - CM0 = -0.0467 - THKMAX = 8.37% - THKMAXE= 8.37% - CMBMAX = 1.50% - XCMAX = 24.19% - XCMAXE = 24.19% - SX = -0.006 - SY = 0.008 + POINTS = 60 + ALFA_0 = -1.878 + CM_0 = -0.0467 + THKMAX = 8.372% + THKMAXE= 8.372% + CMBMAX = 1.504% + XCMAX = 24.186% + XCMAXE = 24.186% + CHORD = 3.747(MAP) + SX = -0.005923 + SY = 0.008150 B0 = -0.000300 A1 = 0.999908 B1 = 0.000293 @@ -5299,3 +5312,1067 @@ Coordinates: test-1093-like-7003.in 0.99679 0.00017 1.00000 0.00000 +************************************ +Running file: test-1095-e423-eppler-to-profoil-conversion.in +************************************ + + 1 AIRFOIL test-1095-e423-eppler-to-profoil-conversion + 2 # Conversion of Eppler's TRA data to a PROFOIL file. + 3 # Ref: Eppler, R, "Airfoil Design and Data", Springer-Verlag, 1990, p304, p554 + 4 # If using this file for design, file "test-1095-e423-profoil-conversion.in" is a better starting point. + 5 + 6 #SKIP_UNKNOWN_WORDS + 7 + 8 COORD 60 + 9 FOIL 16.4 18.7 16.4 18.7 + 10 FOIL 18.4 3 2 3 + 11 FOIL 20.4 10 2 10 + 12 FOIL 21.5 14.7 1.1 14.7 + 13 FOIL 23.5 15.3 2 15.3 + 14 FOIL 25.5 16.2 2 16.2 + 15 FOIL 27.5 17.4 2 17.4 + 16 FOIL 29.5 18.9 2 18.9 + 17 FOIL 31.5 20.7 2 20.7 + 18 FOIL 34.72364 23.2 0 23.2 + 19 FOIL 36.5 10 36.5 10 + 20 FOIL 38.5 12 2 12 + 21 FOIL 40.5 15 2 15 + 22 FOIL 45.5 19 5 19 + 23 FOIL 50.5 11 5 11 + 24 FOIL 55 3 + 25 FOIL 60 3 60 3 + 26 PHIS 5 55 + 27 REC 1 0.00000001 + 28 VLEV 1 1.2 + 29 ILE 10 + 30 + 31 + 32 # Use a cubic spline to find the maximum point for normalization to unit chord. + 33 NORMALIZATION_METHOD 2 + 34 # Slightly rotate normalized airfoil to better match Eppler original airfoil. + 35 ALFA0_BUMP 0.12 + 36 + 37 TOLSPEC 0.00001 + 38 ITERMAX 40 + 39 NOECHO + 40 + 41 # spec KS + 42 NEWT1G0 100 1.0 1 10 + 43 IDES + 44 + 45 + 46 # spec mu u.s. and mu l.s. + 47 NEWT1G0 190 1.0 4 1 0.1 + 48 NEWT1G0 191 0.0 6 100 0.5 + 49 IDES + 50 + 51 # spec omega u.s. + 52 NEWT1G0 194 .66 7 100 0.1 + 53 IDES + 54 + 55 # spec t/c max + 56 NEWT1G0 107 .1234 6 200 .5 + 57 IDES + 58 + 59 + 60 #-------------------------------------------------- + 61 # Evaluate moment and camber. Do not iterate. + 62 TOLSPEC 100 + 63 ITERMAX 0 + 64 NOECHO + 65 NEWT1G0 101 0.0 4 1 0.1 + 66 NEWT1G0 105 0.0 4 1 0.1 + 67 IDES + 68 # Cmo = -0.26653 ... from 101 + 69 # camber = 0.10034 ... from 105 + 70 # K upper = 0.38383 ... from converged dump file + 71 #-------------------------------------------------- + 72 + 73 + 74 FINISH 100 + 75 ALFASP 2 + 76 14 + 77 18 + 78 VELDIST 60 + 79 DUMP + 80 + 81 * + 82 + +************************************ +Output from file: test-1095-e423-eppler-to-profoil-conversion.in +************************************ + + ******************************************** + Airfoil/Comment: test-1095-e423-eppler-to-profoil-conversio + ******************************************** + + ========================================== + Initial airfoil design for stage: 1 + ========================================== + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.773 -0.218 -11.036 -11.553 0.518 1.000 -22.589 + Difference in the design variables: + fnt1_0( 1) = -23.58923 value1() = -22.58923 + RMS error = 23.58922995 Iteration = 0 + Iteration 1 + Calculating partials for airfoil design parameter: 1 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + -0.696 -0.106 0.871 -1.508 1.809 1.000 -0.636 + Difference in the design variables: + fnt1_1( 1) = -1.63618 value1() = -0.63618 deltas() = 2.55962 + RMS error = 1.63617650 Iteration = 1 + Iteration 2 + Calculating partials for airfoil design parameter: 1 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + -0.805 -0.098 1.756 -0.761 1.985 1.000 0.995 + Difference in the design variables: + fnt1_1( 1) = -0.00531 value1() = 0.99469 deltas() = 0.20207 + RMS error = 0.00531004 Iteration = 2 + Iteration 3 + Calculating partials for airfoil design parameter: 1 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + -0.806 -0.098 1.759 -0.759 1.985 1.000 1.000 + Difference in the design variables: + fnt1_1( 1) = -0.00000 value1() = 1.00000 deltas() = 0.00066 + RMS error = 0.00000006 Iteration = 3 + + ========================================== + Initial airfoil design for stage: 2 + ========================================== + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + -0.806 -0.098 1.759 -0.759 1.985 1.000 1.000 + Difference in the design variables: + fnt1_0( 1) = -0.00000 value1() = 1.00000 + fnt1_0( 2) = -1.80579 value1() = -0.80579 + fnt1_0( 3) = -0.09769 value1() = -0.09769 + RMS error = 1.04409691 Iteration = 0 + Iteration 1 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + -0.673 -0.090 1.691 -0.671 1.774 1.000 1.020 + Difference in the design variables: + fnt1_1( 1) = 0.02007 value1() = 1.02007 deltas() = 0.20874 + fnt1_1( 2) = -1.67337 value1() = -0.67337 deltas() = 0.05558 clamp1() = 0.100 + fnt1_1( 3) = -0.09038 value1() = -0.09038 deltas() = 0.50000 clamp1() = 0.500 + RMS error = 0.96759914 Iteration = 1 + Iteration 2 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + -0.544 -0.083 1.624 -0.587 1.589 1.000 1.037 + Difference in the design variables: + fnt1_1( 1) = 0.03683 value1() = 1.03683 deltas() = 0.19847 + fnt1_1( 2) = -1.54444 value1() = -0.54444 deltas() = 0.05650 clamp1() = 0.100 + fnt1_1( 3) = -0.08329 value1() = -0.08329 deltas() = 0.50000 clamp1() = 0.500 + RMS error = 0.89323035 Iteration = 2 + Iteration 3 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + -0.419 -0.076 1.558 -0.507 1.428 1.000 1.051 + Difference in the design variables: + fnt1_1( 1) = 0.05054 value1() = 1.05054 deltas() = 0.18863 + fnt1_1( 2) = -1.41880 value1() = -0.41880 deltas() = 0.05741 clamp1() = 0.100 + fnt1_1( 3) = -0.07640 value1() = -0.07640 deltas() = 0.50000 clamp1() = 0.500 + RMS error = 0.82084777 Iteration = 3 + Iteration 4 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + -0.296 -0.070 1.492 -0.431 1.287 1.000 1.061 + Difference in the design variables: + fnt1_1( 1) = 0.06145 value1() = 1.06145 deltas() = 0.17918 + fnt1_1( 2) = -1.29627 value1() = -0.29627 deltas() = 0.05830 clamp1() = 0.100 + fnt1_1( 3) = -0.06969 value1() = -0.06969 deltas() = 0.50000 clamp1() = 0.500 + RMS error = 0.75032085 Iteration = 4 + Iteration 5 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + -0.177 -0.063 1.427 -0.357 1.162 1.000 1.070 + Difference in the design variables: + fnt1_1( 1) = 0.06977 value1() = 1.06977 deltas() = 0.17011 + fnt1_1( 2) = -1.17669 value1() = -0.17669 deltas() = 0.05919 clamp1() = 0.100 + fnt1_1( 3) = -0.06317 value1() = -0.06317 deltas() = 0.50000 clamp1() = 0.500 + RMS error = 0.68152932 Iteration = 5 + Iteration 6 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + -0.060 -0.057 1.363 -0.287 1.052 1.000 1.076 + Difference in the design variables: + fnt1_1( 1) = 0.07567 value1() = 1.07567 deltas() = 0.16139 + fnt1_1( 2) = -1.05989 value1() = -0.05989 deltas() = 0.06006 clamp1() = 0.100 + fnt1_1( 3) = -0.05681 value1() = -0.05681 deltas() = 0.50000 clamp1() = 0.500 + RMS error = 0.61436160 Iteration = 6 + Iteration 7 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.054 -0.051 1.299 -0.219 0.955 1.000 1.079 + Difference in the design variables: + fnt1_1( 1) = 0.07928 value1() = 1.07928 deltas() = 0.15301 + fnt1_1( 2) = -0.94573 value1() = 0.05427 deltas() = 0.06092 clamp1() = 0.100 + fnt1_1( 3) = -0.05061 value1() = -0.05061 deltas() = 0.50000 clamp1() = 0.500 + RMS error = 0.54871326 Iteration = 7 + Iteration 8 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.166 -0.045 1.235 -0.155 0.868 1.000 1.081 + Difference in the design variables: + fnt1_1( 1) = 0.08073 value1() = 1.08073 deltas() = 0.14493 + fnt1_1( 2) = -0.83407 value1() = 0.16593 deltas() = 0.06177 clamp1() = 0.100 + fnt1_1( 3) = -0.04457 value1() = -0.04457 deltas() = 0.50000 clamp1() = 0.500 + RMS error = 0.48448545 Iteration = 8 + Iteration 9 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.275 -0.039 1.173 -0.093 0.791 1.000 1.080 + Difference in the design variables: + fnt1_1( 1) = 0.08008 value1() = 1.08008 deltas() = 0.13714 + fnt1_1( 2) = -0.72477 value1() = 0.27523 deltas() = 0.06262 clamp1() = 0.100 + fnt1_1( 3) = -0.03866 value1() = -0.03866 deltas() = 0.50000 clamp1() = 0.500 + RMS error = 0.42158330 Iteration = 9 + Iteration 10 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.382 -0.033 1.110 -0.033 0.722 1.000 1.077 + Difference in the design variables: + fnt1_1( 1) = 0.07737 value1() = 1.07737 deltas() = 0.12961 + fnt1_1( 2) = -0.61769 value1() = 0.38231 deltas() = 0.06347 clamp1() = 0.100 + fnt1_1( 3) = -0.03289 value1() = -0.03289 deltas() = 0.50000 clamp1() = 0.500 + RMS error = 0.35991395 Iteration = 10 + Iteration 11 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.487 -0.027 1.048 0.024 0.661 1.000 1.073 + Difference in the design variables: + fnt1_1( 1) = 0.07261 value1() = 1.07261 deltas() = 0.12231 + fnt1_1( 2) = -0.51271 value1() = 0.48729 deltas() = 0.06431 clamp1() = 0.100 + fnt1_1( 3) = -0.02725 value1() = -0.02725 deltas() = 0.50000 clamp1() = 0.500 + RMS error = 0.29938376 Iteration = 11 + Iteration 12 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.590 -0.022 0.987 0.079 0.605 1.000 1.066 + Difference in the design variables: + fnt1_1( 1) = 0.06574 value1() = 1.06574 deltas() = 0.11521 + fnt1_1( 2) = -0.40970 value1() = 0.59030 deltas() = 0.06515 clamp1() = 0.100 + fnt1_1( 3) = -0.02172 value1() = -0.02172 deltas() = 0.50000 clamp1() = 0.500 + RMS error = 0.23989408 Iteration = 12 + Iteration 13 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.691 -0.016 0.925 0.132 0.555 1.000 1.057 + Difference in the design variables: + fnt1_1( 1) = 0.05658 value1() = 1.05658 deltas() = 0.10824 + fnt1_1( 2) = -0.30851 value1() = 0.69149 deltas() = 0.06601 clamp1() = 0.100 + fnt1_1( 3) = -0.01631 value1() = -0.01631 deltas() = 0.50000 clamp1() = 0.500 + RMS error = 0.18133330 Iteration = 13 + Iteration 14 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.791 -0.011 0.863 0.182 0.510 1.000 1.045 + Difference in the design variables: + fnt1_1( 1) = 0.04482 value1() = 1.04482 deltas() = 0.10132 + fnt1_1( 2) = -0.20898 value1() = 0.79102 deltas() = 0.06689 clamp1() = 0.100 + fnt1_1( 3) = -0.01101 value1() = -0.01101 deltas() = 0.50000 clamp1() = 0.500 + RMS error = 0.12355961 Iteration = 14 + Iteration 15 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.889 -0.006 0.800 0.229 0.469 1.000 1.030 + Difference in the design variables: + fnt1_1( 1) = 0.02969 value1() = 1.02969 deltas() = 0.09423 + fnt1_1( 2) = -0.11088 value1() = 0.88912 deltas() = 0.06781 clamp1() = 0.100 + fnt1_1( 3) = -0.00581 value1() = -0.00581 deltas() = 0.50000 clamp1() = 0.500 + RMS error = 0.06635481 Iteration = 15 + Iteration 16 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.986 -0.001 0.735 0.274 0.432 1.000 1.009 + Difference in the design variables: + fnt1_1( 1) = 0.00899 value1() = 1.00899 deltas() = 0.08626 + fnt1_1( 2) = -0.01373 value1() = 0.98627 deltas() = 0.06889 clamp1() = 0.100 + fnt1_1( 3) = -0.00069 value1() = -0.00069 deltas() = 0.50000 clamp1() = 0.500 + RMS error = 0.00948183 Iteration = 16 + Iteration 17 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 1.000 -0.000 0.723 0.277 0.427 1.000 1.000 + Difference in the design variables: + fnt1_1( 1) = 0.00009 value1() = 1.00009 deltas() = 0.00792 + fnt1_1( 2) = -0.00004 value1() = 0.99996 deltas() = 0.00950 clamp1() = 0.100 + fnt1_1( 3) = -0.00000 value1() = -0.00000 deltas() = 0.06549 clamp1() = 0.500 + RMS error = 0.00005418 Iteration = 17 + Iteration 18 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 1.000 -0.000 0.723 0.277 0.427 1.000 1.000 + Difference in the design variables: + fnt1_1( 1) = 0.00000 value1() = 1.00000 deltas() = -0.00004 + fnt1_1( 2) = -0.00000 value1() = 1.00000 deltas() = 0.00002 clamp1() = 0.100 + fnt1_1( 3) = -0.00000 value1() = -0.00000 deltas() = 0.00008 clamp1() = 0.500 + RMS error = 0.00000000 Iteration = 18 + + ========================================== + Initial airfoil design for stage: 3 + ========================================== + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 1.000 -0.000 0.723 0.277 0.427 1.000 1.000 + Difference in the design variables: + fnt1_0( 1) = 0.00000 value1() = 1.00000 + fnt1_0( 2) = -0.00000 value1() = 1.00000 + fnt1_0( 3) = -0.00000 value1() = -0.00000 + fnt1_0( 4) = 0.51177 value1() = 1.00000 + RMS error = 0.25588601 Iteration = 0 + Iteration 1 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Calculating partials for airfoil design parameter: 4 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 1.000 0.000 0.738 0.271 0.438 1.000 1.009 + Difference in the design variables: + fnt1_1( 1) = 0.00903 value1() = 1.00903 deltas() = -0.25651 + fnt1_1( 2) = -0.00043 value1() = 0.99957 deltas() = -0.03026 clamp1() = 0.100 + fnt1_1( 3) = 0.00006 value1() = 0.00006 deltas() = -0.50000 clamp1() = 0.500 + fnt1_1( 4) = 0.49713 value1() = 0.99957 deltas() = -0.04152 clamp1() = 0.100 + RMS error = 0.24860665 Iteration = 1 + Iteration 2 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Calculating partials for airfoil design parameter: 4 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.999 0.000 0.753 0.265 0.449 1.000 1.018 + Difference in the design variables: + fnt1_1( 1) = 0.01812 value1() = 1.01812 deltas() = -0.25913 + fnt1_1( 2) = -0.00088 value1() = 0.99912 deltas() = -0.03042 clamp1() = 0.100 + fnt1_1( 3) = 0.00011 value1() = 0.00011 deltas() = -0.50000 clamp1() = 0.500 + fnt1_1( 4) = 0.48132 value1() = 0.99912 deltas() = -0.04128 clamp1() = 0.100 + RMS error = 0.24083138 Iteration = 2 + Iteration 3 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Calculating partials for airfoil design parameter: 4 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.999 0.000 0.769 0.258 0.460 1.000 1.027 + Difference in the design variables: + fnt1_1( 1) = 0.02722 value1() = 1.02722 deltas() = -0.26181 + fnt1_1( 2) = -0.00136 value1() = 0.99864 deltas() = -0.03057 clamp1() = 0.100 + fnt1_1( 3) = 0.00017 value1() = 0.00017 deltas() = -0.50000 clamp1() = 0.500 + fnt1_1( 4) = 0.46419 value1() = 0.99864 deltas() = -0.04104 clamp1() = 0.100 + RMS error = 0.23249593 Iteration = 3 + Iteration 4 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Calculating partials for airfoil design parameter: 4 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.998 0.000 0.785 0.251 0.472 1.000 1.036 + Difference in the design variables: + fnt1_1( 1) = 0.03628 value1() = 1.03628 deltas() = -0.26456 + fnt1_1( 2) = -0.00186 value1() = 0.99814 deltas() = -0.03073 clamp1() = 0.100 + fnt1_1( 3) = 0.00022 value1() = 0.00022 deltas() = -0.50000 clamp1() = 0.500 + fnt1_1( 4) = 0.44557 value1() = 0.99814 deltas() = -0.04081 clamp1() = 0.100 + RMS error = 0.22352367 Iteration = 4 + Iteration 5 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Calculating partials for airfoil design parameter: 4 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.998 0.000 0.801 0.244 0.485 1.000 1.045 + Difference in the design variables: + fnt1_1( 1) = 0.04521 value1() = 1.04521 deltas() = -0.26737 + fnt1_1( 2) = -0.00239 value1() = 0.99761 deltas() = -0.03088 clamp1() = 0.100 + fnt1_1( 3) = 0.00027 value1() = 0.00027 deltas() = -0.50000 clamp1() = 0.500 + fnt1_1( 4) = 0.42524 value1() = 0.99761 deltas() = -0.04058 clamp1() = 0.100 + RMS error = 0.21382242 Iteration = 5 + Iteration 6 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Calculating partials for airfoil design parameter: 4 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.997 0.000 0.818 0.236 0.498 1.000 1.054 + Difference in the design variables: + fnt1_1( 1) = 0.05389 value1() = 1.05389 deltas() = -0.27025 + fnt1_1( 2) = -0.00294 value1() = 0.99706 deltas() = -0.03104 clamp1() = 0.100 + fnt1_1( 3) = 0.00032 value1() = 0.00032 deltas() = -0.50000 clamp1() = 0.500 + fnt1_1( 4) = 0.40296 value1() = 0.99706 deltas() = -0.04035 clamp1() = 0.100 + RMS error = 0.20328025 Iteration = 6 + Iteration 7 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Calculating partials for airfoil design parameter: 4 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.996 0.000 0.835 0.227 0.512 1.000 1.062 + Difference in the design variables: + fnt1_1( 1) = 0.06216 value1() = 1.06216 deltas() = -0.27321 + fnt1_1( 2) = -0.00351 value1() = 0.99649 deltas() = -0.03119 clamp1() = 0.100 + fnt1_1( 3) = 0.00037 value1() = 0.00037 deltas() = -0.50000 clamp1() = 0.500 + fnt1_1( 4) = 0.37843 value1() = 0.99649 deltas() = -0.04011 clamp1() = 0.100 + RMS error = 0.19175982 Iteration = 7 + Iteration 8 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Calculating partials for airfoil design parameter: 4 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.996 0.000 0.852 0.218 0.526 1.000 1.070 + Difference in the design variables: + fnt1_1( 1) = 0.06980 value1() = 1.06980 deltas() = -0.27625 + fnt1_1( 2) = -0.00408 value1() = 0.99592 deltas() = -0.03134 clamp1() = 0.100 + fnt1_1( 3) = 0.00042 value1() = 0.00042 deltas() = -0.50000 clamp1() = 0.500 + fnt1_1( 4) = 0.35129 value1() = 0.99592 deltas() = -0.03988 clamp1() = 0.100 + RMS error = 0.17909063 Iteration = 8 + Iteration 9 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Calculating partials for airfoil design parameter: 4 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.995 0.000 0.870 0.207 0.542 1.000 1.077 + Difference in the design variables: + fnt1_1( 1) = 0.07651 value1() = 1.07651 deltas() = -0.27938 + fnt1_1( 2) = -0.00465 value1() = 0.99535 deltas() = -0.03149 clamp1() = 0.100 + fnt1_1( 3) = 0.00046 value1() = 0.00046 deltas() = -0.50000 clamp1() = 0.500 + fnt1_1( 4) = 0.32109 value1() = 0.99535 deltas() = -0.03964 clamp1() = 0.100 + RMS error = 0.16505826 Iteration = 9 + Iteration 10 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Calculating partials for airfoil design parameter: 4 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.995 0.000 0.887 0.195 0.558 1.000 1.082 + Difference in the design variables: + fnt1_1( 1) = 0.08185 value1() = 1.08185 deltas() = -0.28261 + fnt1_1( 2) = -0.00519 value1() = 0.99481 deltas() = -0.03164 clamp1() = 0.100 + fnt1_1( 3) = 0.00048 value1() = 0.00048 deltas() = -0.50000 clamp1() = 0.500 + fnt1_1( 4) = 0.28730 value1() = 0.99481 deltas() = -0.03940 clamp1() = 0.100 + RMS error = 0.14938882 Iteration = 10 + Iteration 11 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Calculating partials for airfoil design parameter: 4 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.994 0.001 0.903 0.182 0.574 1.000 1.085 + Difference in the design variables: + fnt1_1( 1) = 0.08516 value1() = 1.08516 deltas() = -0.28595 + fnt1_1( 2) = -0.00564 value1() = 0.99436 deltas() = -0.03179 clamp1() = 0.100 + fnt1_1( 3) = 0.00050 value1() = 0.00050 deltas() = -0.50000 clamp1() = 0.500 + fnt1_1( 4) = 0.24924 value1() = 0.99436 deltas() = -0.03914 clamp1() = 0.100 + RMS error = 0.13172597 Iteration = 11 + Iteration 12 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Calculating partials for airfoil design parameter: 4 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.994 0.001 0.919 0.167 0.592 1.000 1.085 + Difference in the design variables: + fnt1_1( 1) = 0.08547 value1() = 1.08547 deltas() = -0.28944 + fnt1_1( 2) = -0.00595 value1() = 0.99405 deltas() = -0.03194 clamp1() = 0.100 + fnt1_1( 3) = 0.00050 value1() = 0.00050 deltas() = -0.50000 clamp1() = 0.500 + fnt1_1( 4) = 0.20609 value1() = 0.99405 deltas() = -0.03887 clamp1() = 0.100 + RMS error = 0.11159475 Iteration = 12 + Iteration 13 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Calculating partials for airfoil design parameter: 4 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.994 0.000 0.933 0.149 0.611 1.000 1.081 + Difference in the design variables: + fnt1_1( 1) = 0.08118 value1() = 1.08118 deltas() = -0.29312 + fnt1_1( 2) = -0.00599 value1() = 0.99401 deltas() = -0.03210 clamp1() = 0.100 + fnt1_1( 3) = 0.00047 value1() = 0.00047 deltas() = -0.50000 clamp1() = 0.500 + fnt1_1( 4) = 0.15681 value1() = 0.99401 deltas() = -0.03856 clamp1() = 0.100 + RMS error = 0.08833993 Iteration = 13 + Iteration 14 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Calculating partials for airfoil design parameter: 4 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.995 0.000 0.943 0.126 0.630 1.000 1.069 + Difference in the design variables: + fnt1_1( 1) = 0.06941 value1() = 1.06941 deltas() = -0.29711 + fnt1_1( 2) = -0.00548 value1() = 0.99452 deltas() = -0.03226 clamp1() = 0.100 + fnt1_1( 3) = 0.00040 value1() = 0.00040 deltas() = -0.50000 clamp1() = 0.500 + fnt1_1( 4) = 0.10019 value1() = 0.99452 deltas() = -0.03820 clamp1() = 0.100 + RMS error = 0.06100496 Iteration = 14 + Iteration 15 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Calculating partials for airfoil design parameter: 4 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 0.996 0.000 0.947 0.097 0.650 1.000 1.044 + Difference in the design variables: + fnt1_1( 1) = 0.04385 value1() = 1.04385 deltas() = -0.30170 + fnt1_1( 2) = -0.00379 value1() = 0.99621 deltas() = -0.03246 clamp1() = 0.100 + fnt1_1( 3) = 0.00025 value1() = 0.00025 deltas() = -0.50000 clamp1() = 0.500 + fnt1_1( 4) = 0.03499 value1() = 0.99621 deltas() = -0.03772 clamp1() = 0.100 + RMS error = 0.02811123 Iteration = 15 + Iteration 16 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Calculating partials for airfoil design parameter: 4 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 1.000 0.000 0.935 0.069 0.661 1.000 1.004 + Difference in the design variables: + fnt1_1( 1) = 0.00400 value1() = 1.00400 deltas() = -0.16747 + fnt1_1( 2) = -0.00039 value1() = 0.99961 deltas() = -0.01776 clamp1() = 0.100 + fnt1_1( 3) = 0.00002 value1() = 0.00002 deltas() = -0.27111 clamp1() = 0.500 + fnt1_1( 4) = -0.00228 value1() = 0.99961 deltas() = -0.01997 clamp1() = 0.100 + RMS error = 0.00230993 Iteration = 16 + Iteration 17 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Calculating partials for airfoil design parameter: 4 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 1.000 0.000 0.933 0.067 0.660 1.000 1.000 + Difference in the design variables: + fnt1_1( 1) = 0.00001 value1() = 1.00001 deltas() = 0.00626 + fnt1_1( 2) = 0.00000 value1() = 1.00000 deltas() = 0.00070 clamp1() = 0.100 + fnt1_1( 3) = 0.00000 value1() = 0.00000 deltas() = 0.01100 clamp1() = 0.500 + fnt1_1( 4) = -0.00001 value1() = 1.00000 deltas() = 0.00088 clamp1() = 0.100 + RMS error = 0.00000821 Iteration = 17 + + ========================================== + Initial airfoil design for stage: 4 + ========================================== + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 1.000 0.000 0.933 0.067 0.660 1.000 1.000 + Difference in the design variables: + fnt1_0( 1) = 0.00001 value1() = 1.00001 + fnt1_0( 2) = 0.00000 value1() = 1.00000 + fnt1_0( 3) = 0.00000 value1() = 0.00000 + fnt1_0( 4) = -0.00001 value1() = 1.00000 + fnt1_0( 5) = -0.00084 value1() = 0.12256 + RMS error = 0.00037507 Iteration = 0 + Iteration 1 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Calculating partials for airfoil design parameter: 4 + Calculating partials for airfoil design parameter: 5 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 1.004 -0.000 0.900 0.076 0.659 1.000 0.976 + Difference in the design variables: + fnt1_1( 1) = -0.02399 value1() = 0.97601 deltas() = -0.69283 + fnt1_1( 2) = 0.00355 value1() = 1.00355 deltas() = -0.00999 clamp1() = 0.100 + fnt1_1( 3) = -0.00011 value1() = -0.00011 deltas() = -0.35065 clamp1() = 0.500 + fnt1_1( 4) = 0.00355 value1() = 1.00355 deltas() = 0.00000 clamp1() = 0.100 + fnt1_1( 5) = -0.00034 value1() = 0.12306 deltas() = -0.30871 clamp1() = 0.500 + RMS error = 0.01095956 Iteration = 1 + Iteration 2 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Calculating partials for airfoil design parameter: 4 + Calculating partials for airfoil design parameter: 5 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 1.000 -0.000 0.911 0.089 0.660 1.000 1.000 + Difference in the design variables: + fnt1_1( 1) = -0.00011 value1() = 0.99989 deltas() = -0.05422 + fnt1_1( 2) = 0.00002 value1() = 1.00002 deltas() = -0.00083 clamp1() = 0.100 + fnt1_1( 3) = -0.00000 value1() = -0.00000 deltas() = -0.02831 clamp1() = 0.500 + fnt1_1( 4) = 0.00002 value1() = 1.00002 deltas() = 0.00000 clamp1() = 0.100 + fnt1_1( 5) = -0.00000 value1() = 0.12340 deltas() = -0.02599 clamp1() = 0.500 + RMS error = 0.00005083 Iteration = 2 + Iteration 3 + Calculating partials for airfoil design parameter: 1 + Calculating partials for airfoil design parameter: 2 + Calculating partials for airfoil design parameter: 3 + Calculating partials for airfoil design parameter: 4 + Calculating partials for airfoil design parameter: 5 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 1.000 0.000 0.911 0.089 0.660 1.000 1.000 + Difference in the design variables: + fnt1_1( 1) = 0.00000 value1() = 1.00000 deltas() = -0.00231 + fnt1_1( 2) = -0.00000 value1() = 1.00000 deltas() = -0.00003 clamp1() = 0.100 + fnt1_1( 3) = 0.00000 value1() = 0.00000 deltas() = -0.00118 clamp1() = 0.500 + fnt1_1( 4) = -0.00000 value1() = 1.00000 deltas() = 0.00000 clamp1() = 0.100 + fnt1_1( 5) = -0.00000 value1() = 0.12340 deltas() = -0.00105 clamp1() = 0.500 + RMS error = 0.00000043 Iteration = 3 + + ========================================== + Initial airfoil design for stage: 5 + ========================================== + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 1.000 0.000 0.911 0.089 0.660 1.000 1.000 + Difference in the design variables: + fnt1_0( 1) = 0.00000 value1() = 1.00000 + fnt1_0( 2) = -0.00000 value1() = 1.00000 + fnt1_0( 3) = 0.00000 value1() = 0.00000 + fnt1_0( 4) = -0.00000 value1() = 1.00000 + fnt1_0( 5) = -0.00000 value1() = 0.12340 + fnt1_0( 6) = -0.26653 value1() = -0.26653 + fnt1_0( 7) = 0.10034 value1() = 0.10034 + RMS error = 0.10764050 Iteration = 0 + + + ********************** AIRFOIL DESIGN IS FINISHED ********************** + + ****************OUTPUT**************** + * norm x,y -> fort.95 * + * norm x,y -> profoil.xy (high res)* + ************************************** + + Stagnation point falls on coordinate. + *********OUTPUT************** + * v(phi) --> FOR060.DAT * + *********OUTPUT************** + + ************************* + *** WRITING DUMP FILE *** + *** --> profoil.dmp *** + ************************* + + PROFOIL v4.2g October 2024 / MIT License + + **** STATISTICS **** + POINTS = 60 + ALFA_0 = -10.826 + CM_0 = -0.2665 + THKMAX = 12.340% + THKMAXE= 12.340% + CMBMAX = 10.034% + XCMAX = 26.267% + XCMAXE = 26.267% + CHORD = 3.563(MAP) + SX = 0.008890 + SY = 0.002385 + B0 = 0.001400 + A1 = 1.000677 + B1 = -0.001279 + ******************** + + + +============================================ +Dump File: test-1095-e423-eppler-to-profoil-conversion.in +============================================ + +FOIL 16.40000 18.62533 1 +FOIL 18.40000 2.92533 2 +FOIL 20.40000 9.92533 3 +FOIL 21.50000 14.62533 4 +FOIL 23.50000 15.22533 5 +FOIL 25.50000 16.12533 6 +FOIL 27.50000 17.32533 7 +FOIL 29.50000 18.82533 8 +FOIL 31.50000 20.62533 9 +FOIL 34.72364 23.12533 10 +FOIL 36.50000 9.66425 11 +FOIL 38.50000 11.66425 12 +FOIL 40.50000 14.66425 13 +FOIL 45.50000 18.66425 14 +FOIL 50.50000 10.66425 15 +FOIL 55.00000 2.66425 16 +FOIL 60.00000 2.66425 17 +PHIS 5.00000 55.00000 +REC 0.38383 0.00000 +VLEV 1 1.70640 +ILE 10 + +============================================ +Coordinates: test-1095-e423-eppler-to-profoil-conversion.in +============================================ + + 1.00000 0.00000 + 0.99646 0.00152 + 0.98683 0.00643 + 0.97274 0.01433 + 0.95500 0.02385 + 0.93331 0.03377 + 0.90705 0.04394 + 0.87636 0.05471 + 0.84181 0.06608 + 0.80392 0.07789 + 0.76325 0.08994 + 0.72038 0.10199 + 0.67588 0.11375 + 0.63034 0.12490 + 0.58431 0.13510 + 0.53832 0.14398 + 0.49288 0.15111 + 0.44814 0.15591 + 0.40410 0.15825 + 0.36098 0.15823 + 0.31898 0.15588 + 0.27839 0.15137 + 0.23945 0.14482 + 0.20246 0.13655 + 0.16780 0.12674 + 0.13578 0.11562 + 0.10670 0.10338 + 0.08081 0.09026 + 0.05831 0.07651 + 0.03936 0.06239 + 0.02409 0.04821 + 0.01256 0.03429 + 0.00481 0.02104 + 0.00077 0.00889 + 0.00028 -0.00137 + 0.00439 -0.00831 + 0.01421 -0.01243 + 0.02958 -0.01464 + 0.05022 -0.01466 + 0.07613 -0.01223 + 0.10753 -0.00732 + 0.14468 0.00006 + 0.18808 0.00940 + 0.23772 0.01931 + 0.29279 0.02883 + 0.35246 0.03712 + 0.41534 0.04303 + 0.47950 0.04632 + 0.54349 0.04761 + 0.60644 0.04712 + 0.66747 0.04500 + 0.72553 0.04124 + 0.77953 0.03619 + 0.82867 0.03044 + 0.87241 0.02440 + 0.91026 0.01843 + 0.94186 0.01289 + 0.96695 0.00801 + 0.98521 0.00398 + 0.99631 0.00112 + 1.00000 -0.00000 + +************************************ +Running file: test-1096-e423-profoil-conversion.in +************************************ + + 1 AIRFOIL test-1096-e423-profoil-conversion + 2 # Generated from "test-e423-eppler-to-profoil-conversion.in" and its output. + 3 + 4 #SKIP_UNKNOWN_WORDS + 5 + 6 COORD 60 + 7 FOIL 16.40000 18.62533 1 + 8 FOIL 18.40000 2.92533 2 + 9 FOIL 20.40000 9.92533 3 + 10 FOIL 21.50000 14.62533 4 + 11 FOIL 23.50000 15.22533 5 + 12 FOIL 25.50000 16.12533 6 + 13 FOIL 27.50000 17.32533 7 + 14 FOIL 29.50000 18.82533 8 + 15 FOIL 31.50000 20.62533 9 + 16 FOIL 34.72364 23.12533 10 + 17 FOIL 36.50000 9.66425 11 + 18 FOIL 38.50000 11.66425 12 + 19 FOIL 40.50000 14.66425 13 + 20 FOIL 45.50000 18.66425 14 + 21 FOIL 50.50000 10.66425 15 + 22 FOIL 55.00000 2.66425 16 + 23 FOIL 60.00000 2.66425 17 + 24 PHIS 5.00000 55.00000 + 25 REC 0.38383 0.00000001 + 26 VLEV 1 1.70640 + 27 ILE 10 + 28 + 29 + 30 # Use a cubic spline to find the maximum point for normalization to unit chord. + 31 NORMALIZATION_METHOD 2 + 32 # Comment out next line if using this file as a starting point for a new design. + 33 ALFA0_BUMP 0.12 + 34 + 35 TOLSPEC 0.00001 + 36 ITERMAX 40 + 37 NOECHO + 38 + 39 # spec KS + 40 NEWT1G0 100 1.0 1 10 + 41 IDES + 42 + 43 # spec Cmo + 44 NEWT1G0 101 -0.26653 4 1 0.1 + 45 IDES + 46 + 47 # spec t/c max + 48 NEWT1G0 107 .1234 6 300 .5 + 49 IDES + 50 + 51 + 52 + 53 + 54 FINISH 100 + 55 ALFASP 2 + 56 14 + 57 18 + 58 VELDIST 60 + 59 DUMP + 60 + 61 * + 62 + +************************************ +Output from file: test-1096-e423-profoil-conversion.in +************************************ + + ******************************************** + Airfoil/Comment: test-1096-e423-profoil-conversion + ******************************************** + + ========================================== + Initial airfoil design for stage: 1 + ========================================== + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 1.000 -0.000 0.911 0.089 0.660 1.000 1.000 + Difference in the design variables: + fnt1_0( 1) = -0.00028 value1() = 0.99972 + RMS error = 0.00028320 Iteration = 0 + Iteration 1 + Calculating partials for airfoil design parameter: 1 + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 1.000 -0.000 0.911 0.089 0.660 1.000 1.000 + Difference in the design variables: + fnt1_1( 1) = -0.00000 value1() = 1.00000 deltas() = 0.00003 + RMS error = 0.00000000 Iteration = 1 + + ========================================== + Initial airfoil design for stage: 2 + ========================================== + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 1.000 -0.000 0.911 0.089 0.660 1.000 1.000 + Difference in the design variables: + fnt1_0( 1) = -0.00000 value1() = 1.00000 + fnt1_0( 2) = 0.00000 value1() = -0.26653 + RMS error = 0.00000128 Iteration = 0 + + ========================================== + Initial airfoil design for stage: 3 + ========================================== + Total airfoil design: + UMU(1) UMU(2) HKH(1) HKH(2) OMEGA(1) OMEGA(2) SKS + 1.000 -0.000 0.911 0.089 0.660 1.000 1.000 + Difference in the design variables: + fnt1_0( 1) = -0.00000 value1() = 1.00000 + fnt1_0( 2) = 0.00000 value1() = -0.26653 + fnt1_0( 3) = -0.00000 value1() = 0.12340 + RMS error = 0.00000117 Iteration = 0 + + + ********************** AIRFOIL DESIGN IS FINISHED ********************** + + ****************OUTPUT**************** + * norm x,y -> fort.95 * + * norm x,y -> profoil.xy (high res)* + ************************************** + + Stagnation point falls on coordinate. + *********OUTPUT************** + * v(phi) --> FOR060.DAT * + *********OUTPUT************** + + ************************* + *** WRITING DUMP FILE *** + *** --> profoil.dmp *** + ************************* + + PROFOIL v4.2g October 2024 / MIT License + + **** STATISTICS **** + POINTS = 60 + ALFA_0 = -10.826 + CM_0 = -0.2665 + THKMAX = 12.340% + THKMAXE= 12.340% + CMBMAX = 10.034% + XCMAX = 26.267% + XCMAXE = 26.267% + CHORD = 3.563(MAP) + SX = 0.008890 + SY = 0.002250 + B0 = 0.001400 + A1 = 1.000675 + B1 = -0.001279 + ******************** + + + +============================================ +Dump File: test-1096-e423-profoil-conversion.in +============================================ + +FOIL 16.40000 18.62533 1 +FOIL 18.40000 2.92533 2 +FOIL 20.40000 9.92533 3 +FOIL 21.50000 14.62533 4 +FOIL 23.50000 15.22533 5 +FOIL 25.50000 16.12533 6 +FOIL 27.50000 17.32533 7 +FOIL 29.50000 18.82533 8 +FOIL 31.50000 20.62533 9 +FOIL 34.72365 23.12533 10 +FOIL 36.50000 9.66425 11 +FOIL 38.50000 11.66425 12 +FOIL 40.50000 14.66425 13 +FOIL 45.50000 18.66425 14 +FOIL 50.50000 10.66425 15 +FOIL 55.00000 2.66425 16 +FOIL 60.00000 2.66425 17 +PHIS 5.00000 55.00000 +REC 0.38383 0.00000 +VLEV 1 1.70640 +ILE 10 + +============================================ +Coordinates: test-1096-e423-profoil-conversion.in +============================================ + + 1.00000 0.00000 + 0.99646 0.00152 + 0.98684 0.00643 + 0.97274 0.01433 + 0.95500 0.02385 + 0.93331 0.03377 + 0.90705 0.04394 + 0.87636 0.05471 + 0.84181 0.06608 + 0.80392 0.07789 + 0.76325 0.08994 + 0.72038 0.10199 + 0.67588 0.11375 + 0.63034 0.12490 + 0.58431 0.13510 + 0.53832 0.14398 + 0.49288 0.15111 + 0.44814 0.15591 + 0.40410 0.15825 + 0.36098 0.15823 + 0.31898 0.15588 + 0.27839 0.15137 + 0.23945 0.14482 + 0.20246 0.13655 + 0.16780 0.12674 + 0.13578 0.11562 + 0.10670 0.10338 + 0.08081 0.09026 + 0.05831 0.07651 + 0.03936 0.06239 + 0.02409 0.04821 + 0.01256 0.03429 + 0.00481 0.02104 + 0.00077 0.00889 + 0.00028 -0.00137 + 0.00439 -0.00831 + 0.01421 -0.01243 + 0.02958 -0.01464 + 0.05022 -0.01466 + 0.07613 -0.01223 + 0.10753 -0.00732 + 0.14468 0.00006 + 0.18808 0.00940 + 0.23772 0.01931 + 0.29279 0.02883 + 0.35246 0.03712 + 0.41534 0.04303 + 0.47950 0.04632 + 0.54349 0.04761 + 0.60644 0.04712 + 0.66747 0.04500 + 0.72553 0.04124 + 0.77953 0.03619 + 0.82867 0.03044 + 0.87241 0.02440 + 0.91026 0.01843 + 0.94186 0.01289 + 0.96695 0.00801 + 0.98521 0.00398 + 0.99631 0.00112 + 1.00000 0.00000 + diff --git a/src/test/results-gfortran/profoil_test_short.txt b/src/test/results-gfortran/profoil_test_short.txt index 97a00b5..ab96ee4 100644 --- a/src/test/results-gfortran/profoil_test_short.txt +++ b/src/test/results-gfortran/profoil_test_short.txt @@ -1,4 +1,4 @@ -Thu Nov 24 21:56:45 CST 2022 +Sat Oct 5 20:30:01 CDT 2024 ============================================ Dump File: test-1000-four-seg.in ============================================ @@ -1674,3 +1674,187 @@ Coordinates: test-1093-like-7003.in 0.99679 0.00017 1.00000 0.00000 +============================================ +Dump File: test-1095-e423-eppler-to-profoil-conversion.in +============================================ + +FOIL 16.40000 18.62533 1 +FOIL 18.40000 2.92533 2 +FOIL 20.40000 9.92533 3 +FOIL 21.50000 14.62533 4 +FOIL 23.50000 15.22533 5 +FOIL 25.50000 16.12533 6 +FOIL 27.50000 17.32533 7 +FOIL 29.50000 18.82533 8 +FOIL 31.50000 20.62533 9 +FOIL 34.72364 23.12533 10 +FOIL 36.50000 9.66425 11 +FOIL 38.50000 11.66425 12 +FOIL 40.50000 14.66425 13 +FOIL 45.50000 18.66425 14 +FOIL 50.50000 10.66425 15 +FOIL 55.00000 2.66425 16 +FOIL 60.00000 2.66425 17 +PHIS 5.00000 55.00000 +REC 0.38383 0.00000 +VLEV 1 1.70640 +ILE 10 + +============================================ +Coordinates: test-1095-e423-eppler-to-profoil-conversion.in +============================================ + + 1.00000 0.00000 + 0.99646 0.00152 + 0.98683 0.00643 + 0.97274 0.01433 + 0.95500 0.02385 + 0.93331 0.03377 + 0.90705 0.04394 + 0.87636 0.05471 + 0.84181 0.06608 + 0.80392 0.07789 + 0.76325 0.08994 + 0.72038 0.10199 + 0.67588 0.11375 + 0.63034 0.12490 + 0.58431 0.13510 + 0.53832 0.14398 + 0.49288 0.15111 + 0.44814 0.15591 + 0.40410 0.15825 + 0.36098 0.15823 + 0.31898 0.15588 + 0.27839 0.15137 + 0.23945 0.14482 + 0.20246 0.13655 + 0.16780 0.12674 + 0.13578 0.11562 + 0.10670 0.10338 + 0.08081 0.09026 + 0.05831 0.07651 + 0.03936 0.06239 + 0.02409 0.04821 + 0.01256 0.03429 + 0.00481 0.02104 + 0.00077 0.00889 + 0.00028 -0.00137 + 0.00439 -0.00831 + 0.01421 -0.01243 + 0.02958 -0.01464 + 0.05022 -0.01466 + 0.07613 -0.01223 + 0.10753 -0.00732 + 0.14468 0.00006 + 0.18808 0.00940 + 0.23772 0.01931 + 0.29279 0.02883 + 0.35246 0.03712 + 0.41534 0.04303 + 0.47950 0.04632 + 0.54349 0.04761 + 0.60644 0.04712 + 0.66747 0.04500 + 0.72553 0.04124 + 0.77953 0.03619 + 0.82867 0.03044 + 0.87241 0.02440 + 0.91026 0.01843 + 0.94186 0.01289 + 0.96695 0.00801 + 0.98521 0.00398 + 0.99631 0.00112 + 1.00000 -0.00000 + +============================================ +Dump File: test-1096-e423-profoil-conversion.in +============================================ + +FOIL 16.40000 18.62533 1 +FOIL 18.40000 2.92533 2 +FOIL 20.40000 9.92533 3 +FOIL 21.50000 14.62533 4 +FOIL 23.50000 15.22533 5 +FOIL 25.50000 16.12533 6 +FOIL 27.50000 17.32533 7 +FOIL 29.50000 18.82533 8 +FOIL 31.50000 20.62533 9 +FOIL 34.72365 23.12533 10 +FOIL 36.50000 9.66425 11 +FOIL 38.50000 11.66425 12 +FOIL 40.50000 14.66425 13 +FOIL 45.50000 18.66425 14 +FOIL 50.50000 10.66425 15 +FOIL 55.00000 2.66425 16 +FOIL 60.00000 2.66425 17 +PHIS 5.00000 55.00000 +REC 0.38383 0.00000 +VLEV 1 1.70640 +ILE 10 + +============================================ +Coordinates: test-1096-e423-profoil-conversion.in +============================================ + + 1.00000 0.00000 + 0.99646 0.00152 + 0.98684 0.00643 + 0.97274 0.01433 + 0.95500 0.02385 + 0.93331 0.03377 + 0.90705 0.04394 + 0.87636 0.05471 + 0.84181 0.06608 + 0.80392 0.07789 + 0.76325 0.08994 + 0.72038 0.10199 + 0.67588 0.11375 + 0.63034 0.12490 + 0.58431 0.13510 + 0.53832 0.14398 + 0.49288 0.15111 + 0.44814 0.15591 + 0.40410 0.15825 + 0.36098 0.15823 + 0.31898 0.15588 + 0.27839 0.15137 + 0.23945 0.14482 + 0.20246 0.13655 + 0.16780 0.12674 + 0.13578 0.11562 + 0.10670 0.10338 + 0.08081 0.09026 + 0.05831 0.07651 + 0.03936 0.06239 + 0.02409 0.04821 + 0.01256 0.03429 + 0.00481 0.02104 + 0.00077 0.00889 + 0.00028 -0.00137 + 0.00439 -0.00831 + 0.01421 -0.01243 + 0.02958 -0.01464 + 0.05022 -0.01466 + 0.07613 -0.01223 + 0.10753 -0.00732 + 0.14468 0.00006 + 0.18808 0.00940 + 0.23772 0.01931 + 0.29279 0.02883 + 0.35246 0.03712 + 0.41534 0.04303 + 0.47950 0.04632 + 0.54349 0.04761 + 0.60644 0.04712 + 0.66747 0.04500 + 0.72553 0.04124 + 0.77953 0.03619 + 0.82867 0.03044 + 0.87241 0.02440 + 0.91026 0.01843 + 0.94186 0.01289 + 0.96695 0.00801 + 0.98521 0.00398 + 0.99631 0.00112 + 1.00000 0.00000 + diff --git a/src/test/results-gfortran/profoil_test_tra.txt b/src/test/results-gfortran/profoil_test_tra.txt index 2d95765..b6ee5ee 100644 --- a/src/test/results-gfortran/profoil_test_tra.txt +++ b/src/test/results-gfortran/profoil_test_tra.txt @@ -1,4 +1,4 @@ -Thu Nov 24 21:56:45 CST 2022 +Sat Oct 5 20:30:01 CDT 2024 ************************************ Running file: test-1030-many-segments-and-tra.in ************************************ @@ -10,7 +10,7 @@ Eppler style output - PROFOIL Version 2.0 March 2022 + PROFOIL Version 4.2g October 2024 ITERATION 0