********************************************************************* * * * PROGRAM TSFOIL * * SOLVES * * INVISCID FLOW PAST THIN TWO DIMENSIONAL LIFTING AIRFOIL * * USING * * TRANSONIC SMALL DISTURBANCE THEORY * * FULLY CONSERVATIVE FINITE DIFFERENCE EQUATIONS * * SUCCESSIVE LINE OVERRELAXATION * * * * WRITTEN BY * * * * EARLL M. MURMAN AND FRANK R. BAILEY * * NASA-AMES RESEARCH CENTER * * MOFFETT FIELD, CALIFORNIA * * AND * * MARGARET L. JOHNSON * * COMPUTER SCIENCES CORPORATION * * MOUNTAIN VIEW, CALIFORNIA * * * ********************************************************************* enter name of input data file N0012.inp NACA 0012 EMACH = 0.75000 POR = 0.00000 IMIN = 1 BCTYPE = 1 AMESH = T DELTA = 0.12000 CLSET = 0.00000 IMAXI = 81 BCFOIL = 1 PHYS = T ALPHA = 2.00000 EPS = 0.20000 JMIN = 1 PSTART = 1 PSAVE = F AK = 0.00000 RIGF = 0.00000 JMAXI = 64 PRTFLO = 1 KUTTA = T GAM = 1.40000 WCIRC = 1.00000 MAXIT =1500 IPRTER = 10 FCR = T F = 0.00000 CVERGE = 0.00001 NU = 100 SIMDEF = 3 H = 0.00000 DVERGE = 10.0 NL = 75 ICUT = 2 WE = 1.80,1.90,1.95 XIN -4.759090 -1.451373 -1.154130 -0.959227 -0.798421 -0.644242 -0.473078 -0.290925 -0.176356 -0.113082 -0.074485 -0.049489 -0.032465 -0.020228 -0.010907 -0.003416 0.002981 0.008679 0.014039 0.019292 0.024707 0.030523 0.037083 0.044772 0.054190 0.066066 0.081200 0.100083 0.122447 0.147263 0.173324 0.199723 0.225942 0.251747 0.277060 0.301889 0.326276 0.350282 0.373966 0.397389 0.420605 0.443660 0.466597 0.489449 0.512245 0.535006 0.557751 0.580493 0.603241 0.626005 0.648791 0.671609 0.694470 0.717388 0.740383 0.763482 0.786719 0.810138 0.833793 0.857753 0.882101 0.906941 0.932402 0.958646 0.985879 1.014370 1.044481 1.076713 1.111798 1.150867 1.195818 1.250238 1.322245 1.436261 1.647911 1.849817 2.013718 2.177861 2.372788 2.664829 4.821552 YIN -5.200000 -2.594099 -1.722835 -1.285221 -1.021059 -0.843610 -0.715700 -0.618740 -0.542401 -0.480483 -0.429040 -0.385438 -0.347855 -0.314984 -0.285868 -0.259787 -0.236187 -0.214639 -0.194798 -0.176391 -0.159191 -0.143013 -0.127701 -0.113124 -0.099167 -0.085732 -0.072733 -0.060093 -0.047741 -0.035615 -0.023653 -0.011800 0.011800 0.023653 0.035615 0.047741 0.060093 0.072733 0.085732 0.099167 0.113124 0.127701 0.143013 0.159191 0.176391 0.194798 0.214639 0.236187 0.259787 0.285868 0.314984 0.347855 0.385438 0.429040 0.480483 0.542401 0.618740 0.715700 0.843610 1.021059 1.285221 1.722835 2.594099 5.200000 SCALED POR= 0.00000 AIRFOIL GEOMETRY INFORMATION PRINTOUT IN PHYSICAL VARIABLES NORMALIZED BY CHORD LENGTH MAX THICKNESS = 0.120033 AIRFOIL VOLUME = 0.08210815 MAX CAMBER = 0.000000 UPPER SURFACE LOWER SURFACE X Y DY/DX Y DY/DX THICKNESS CAMBER 0.00298125 0.00949933 1.55444193 -0.00949933 -1.55444193 0.00949933 0.00000000 0.00867915 0.01592395 0.87685335 -0.01592395 -0.87685335 0.01592395 0.00000000 0.01403880 0.02000455 0.67031479 -0.02000455 -0.67031479 0.02000455 0.00000000 0.01929164 0.02320689 0.55772793 -0.02320689 -0.55772793 0.02320689 0.00000000 0.02470696 0.02600677 0.48094332 -0.02600677 -0.48094332 0.02600677 0.00000000 0.03052330 0.02862338 0.42181006 -0.02862338 -0.42181006 0.02862338 0.00000000 0.03708321 0.03121941 0.37197819 -0.03121941 -0.37197819 0.03121941 0.00000000 0.04477173 0.03390068 0.32746285 -0.03390068 -0.32746285 0.03390068 0.00000000 0.05419004 0.03677912 0.28562370 -0.03677912 -0.28562370 0.03677912 0.00000000 0.06606644 0.03992064 0.24521872 -0.03992064 -0.24521872 0.03992064 0.00000000 0.08119977 0.04332104 0.20595875 -0.04332104 -0.20595875 0.04332104 0.00000000 0.10008341 0.04684177 0.16860121 -0.04684177 -0.16860121 0.04684177 0.00000000 0.12244672 0.05021497 0.13450375 -0.05021497 -0.13450375 0.05021497 0.00000000 0.14726296 0.05316905 0.10469174 -0.05316905 -0.10469174 0.05316905 0.00000000 0.17332384 0.05555602 0.07932116 -0.05555602 -0.07932116 0.05555602 0.00000000 0.19972268 0.05735940 0.05790997 -0.05735940 -0.05790997 0.05735940 0.00000000 0.22594240 0.05863407 0.03976896 -0.05863407 -0.03976896 0.05863407 0.00000000 0.25174683 0.05945564 0.02424954 -0.05945564 -0.02424954 0.05945564 0.00000000 0.27706018 0.05989614 0.01082146 -0.05989614 -0.01082146 0.05989614 0.00000000 0.30188873 0.06001632 -0.00092743 -0.06001632 0.00092743 0.06001632 0.00000000 0.32627636 0.05986491 -0.01131261 -0.05986491 0.01131261 0.05986491 0.00000000 0.35028163 0.05948040 -0.02057608 -0.05948040 0.02057608 0.05948040 0.00000000 0.37396622 0.05889295 -0.02890516 -0.05889295 0.02890516 0.05889295 0.00000000 0.39738923 0.05812630 -0.03644662 -0.05812630 0.03644662 0.05812630 0.00000000 0.42060480 0.05719933 -0.04331724 -0.05719933 0.04331724 0.05719933 0.00000000 0.44366038 0.05612711 -0.04961109 -0.05612711 0.04961109 0.05612711 0.00000000 0.46659705 0.05492191 -0.05540533 -0.05492191 0.05540533 0.05492191 0.00000000 0.48944914 0.05359381 -0.06076401 -0.05359381 0.06076401 0.05359381 0.00000000 0.51224482 0.05215126 -0.06574143 -0.05215126 0.06574143 0.05215126 0.00000000 0.53500640 0.05060146 -0.07038424 -0.05060146 0.07038424 0.05060146 0.00000000 0.55775130 0.04895060 -0.07473329 -0.04895060 0.07473329 0.04895060 0.00000000 0.58049279 0.04720407 -0.07882507 -0.04720407 0.07882507 0.04720407 0.00000000 0.60324109 0.04536654 -0.08269273 -0.04536654 0.08269273 0.04536654 0.00000000 0.62600458 0.04344200 -0.08636699 -0.04344200 0.08636699 0.04344200 0.00000000 0.64879102 0.04143373 -0.08987672 -0.04143373 0.08987672 0.04143373 0.00000000 0.67160910 0.03934419 -0.09324961 -0.03934419 0.09324961 0.03934419 0.00000000 0.69446981 0.03717494 -0.09651251 -0.03717494 0.09651251 0.03717494 0.00000000 0.71738797 0.03492647 -0.09969195 -0.03492647 0.09969195 0.03492647 0.00000000 0.74038333 0.03259800 -0.10281438 -0.03259800 0.10281438 0.03259800 0.00000000 0.76348239 0.03018731 -0.10590672 -0.03018731 0.10590672 0.03018731 0.00000000 0.78671944 0.02769044 -0.10899668 -0.02769044 0.10899668 0.02769044 0.00000000 0.81013811 0.02510142 -0.11211339 -0.02510142 0.11211339 0.02510142 0.00000000 0.83379328 0.02241188 -0.11528805 -0.02241188 0.11528805 0.02241188 0.00000000 0.85775286 0.01961062 -0.11855497 -0.01961062 0.11855497 0.01961062 0.00000000 0.88210094 0.01668286 -0.12195269 -0.01668286 0.12195269 0.01668286 0.00000000 0.90694106 0.01360941 -0.12552573 -0.01360941 0.12552573 0.01360941 0.00000000 0.93240225 0.01036530 -0.12932716 -0.01036530 0.12932716 0.01036530 0.00000000 0.95864606 0.00691795 -0.13342194 -0.00691795 0.13342194 0.00691795 0.00000000 0.98587894 0.00322418 -0.13789238 -0.00322418 0.13789238 0.00322418 0.00000000 WE = 1.8000 EPS = 0.2000 MAXIT FOR THIS MESH = 375 ITER CL CM IERR JERR ERROR IRL JRL BIGRL ERCIRC 10 0.33338 -0.02625 12 8 0.3957E-01 5 8 0.1062E+03 0.3074E-01 20 0.38159 -0.00450 5 3 0.1157E-01 5 8 0.7293E+02 0.3300E-02 30 0.41479 -0.00209 12 8 0.7819E-02 5 8 0.4942E+02 0.4917E-02 40 0.44250 -0.00539 20 8 0.5126E-01 20 8 0.6365E+02 0.3701E-01 50 0.46015 -0.00724 20 8 0.6510E-01 20 8 0.7962E+02 0.4901E-01 60 0.47262 -0.00858 20 8 0.7809E-01 20 8 0.9529E+02 0.5961E-01 70 0.48248 -0.00988 20 8 0.8889E-01 20 8 0.1083E+03 0.6809E-01 80 0.49023 -0.01099 20 8 0.9713E-01 20 8 0.1183E+03 0.7461E-01 90 0.49623 -0.01190 20 8 0.1034E+00 20 8 0.1259E+03 0.7954E-01 100 0.50090 -0.01264 20 8 0.1082E+00 20 8 0.1317E+03 0.8334E-01 110 0.50450 -0.01321 20 8 0.1118E+00 20 8 0.1361E+03 0.8627E-01 120 0.50727 -0.01365 20 8 0.1147E+00 20 8 0.1396E+03 0.8855E-01 130 0.50940 -0.01400 20 8 0.1169E+00 20 8 0.1423E+03 0.9031E-01 140 0.51105 -0.01428 20 8 0.1186E+00 20 8 0.1443E+03 0.9166E-01 150 0.51232 -0.01449 20 8 0.1199E+00 20 8 0.1459E+03 0.9270E-01 160 0.51330 -0.01466 20 8 0.1209E+00 20 8 0.1471E+03 0.9350E-01 170 0.51407 -0.01479 20 8 0.1217E+00 20 8 0.1481E+03 0.9412E-01 180 0.51465 -0.01489 20 8 0.1223E+00 20 8 0.1488E+03 0.9460E-01 190 0.51511 -0.01497 20 8 0.1228E+00 20 8 0.1494E+03 0.9497E-01 200 0.51546 -0.01503 20 8 0.1232E+00 20 8 0.1498E+03 0.9526E-01 210 0.51573 -0.01508 20 8 0.1234E+00 20 8 0.1502E+03 0.9548E-01 220 0.51594 -0.01512 20 8 0.1237E+00 20 8 0.1504E+03 0.9565E-01 230 0.51611 -0.01514 20 8 0.1238E+00 20 8 0.1506E+03 0.9579E-01 240 0.51623 -0.01516 20 8 0.1240E+00 20 8 0.1508E+03 0.9589E-01 250 0.51633 -0.01518 20 8 0.1241E+00 20 8 0.1509E+03 0.9597E-01 260 0.51640 -0.01519 20 8 0.1241E+00 20 8 0.1510E+03 0.9603E-01 270 0.51646 -0.01520 20 8 0.1242E+00 20 8 0.1511E+03 0.9608E-01 280 0.51651 -0.01521 20 8 0.1242E+00 20 8 0.1511E+03 0.9611E-01 290 0.51654 -0.01522 20 8 0.1243E+00 20 8 0.1512E+03 0.9614E-01 300 0.51657 -0.01522 20 8 0.1243E+00 20 8 0.1512E+03 0.9616E-01 310 0.51659 -0.01523 20 8 0.1243E+00 20 8 0.1512E+03 0.9618E-01 320 0.51661 -0.01523 20 8 0.1243E+00 20 8 0.1513E+03 0.9619E-01 330 0.51662 -0.01523 20 8 0.1244E+00 20 8 0.1513E+03 0.9620E-01 340 0.51663 -0.01523 20 8 0.1244E+00 20 8 0.1513E+03 0.9621E-01 350 0.51663 -0.01523 20 8 0.1244E+00 20 8 0.1513E+03 0.9622E-01 360 0.51664 -0.01523 20 8 0.1244E+00 20 8 0.1513E+03 0.9622E-01 370 0.51664 -0.01524 20 8 0.1244E+00 20 8 0.1513E+03 0.9623E-01 ****** ITERATION LIMIT REACHED ****** FORCE COEFFICIENTS, PRESSURE COEFFICIENT, AND MACH NUMBER (OR SIMILARITY PARAMETER) ON BODY AND DIVIDING STREAM LINE. COARSE MESH CL = 0.458548 CM = -0.012157 CP* = -0.603170 LOWER UPPER Y=0- Y=0+ I X CP M1 CP M1 1 -4.759090 -0.053779 0.775569 -0.053779 0.775569 B * 2 -0.798421 0.088298 0.706013 0.088298 0.706013 B * 3 -0.176356 0.382637 0.533817 0.382637 0.533817 B * 4 -0.032465 0.829335 0.000000 0.829335 0.000000 B * AIRFOIL LEADING EDGE AIRFOIL LEADING EDGE 5 0.002981 0.933341 0.000000 0.557376 0.397764 L U * 6 0.024707 -0.157400 0.822598 -0.845895 1.084461 L * U 7 0.054190 -0.441048 0.939365 -1.290529 1.224159 L * U 8 0.122447 -0.536604 0.975560 -1.255236 1.213658 L* U 9 0.225942 -0.493676 0.959469 -1.285975 1.222809 L * U 10 0.326276 -0.414934 0.929229 -1.300897 1.227227 L * U 11 0.420605 -0.341175 0.899981 -1.282696 1.221836 L * U 12 0.512245 -0.249968 0.862444 -0.800716 1.069246 L * U 13 0.603241 -0.131368 0.811040 -0.255467 0.864754 L U * 14 0.694470 -0.090664 0.792630 -0.106891 0.800020 B * 15 0.786719 0.012045 0.744153 -0.100548 0.797139 L U * 16 0.882101 0.055019 0.722906 0.049676 0.725581 B * 17 0.985879 0.353334 0.553367 0.151355 0.672843 L U * AIRFOIL TRAILING EDGE AIRFOIL TRAILING EDGE 18 1.111798 0.232683 0.627477 0.232683 0.627477 B * 19 1.322245 0.088785 0.705763 0.088785 0.705763 B * 20 2.013718 0.016061 0.742193 0.016061 0.742193 B * 21 4.821552 -0.018545 0.758914 -0.018545 0.758914 B * Y(J) J= 1 TO 16 -5.200000 -1.021059 -0.542401 -0.347855 -0.236187 -0.159191 -0.099167 -0.047741 0.047741 0.099167 0.159191 0.236187 0.347855 0.542401 1.021059 5.200000 WE = 1.9000 EPS = 0.2000 MAXIT FOR THIS MESH = 750 ITER CL CM IERR JERR ERROR IRL JRL BIGRL ERCIRC 10 0.51493 -0.02727 29 18 0.1152E-01 9 16 0.1468E+03 0.6480E-02 20 0.54120 -0.02754 25 16 0.2844E-02 9 16 0.6822E+02 0.3701E-02 30 0.54796 -0.02341 8 27 0.1341E-02 9 17 0.3005E+02 0.1016E-02 40 0.54484 -0.02108 22 17 0.7493E-03 9 17 0.1346E+02 0.6664E-03 50 0.54251 -0.02048 19 17 0.8811E-03 9 17 0.8375E+01 0.7142E-03 60 0.54148 -0.02042 16 17 0.9600E-03 9 16 0.1333E+02 0.6865E-03 70 0.54030 -0.02017 14 17 0.8904E-03 9 16 0.1301E+02 0.6229E-03 80 0.53889 -0.01980 14 17 0.7839E-03 9 16 0.1036E+02 0.5410E-03 90 0.53746 -0.01950 13 17 0.7084E-03 9 17 0.8791E+01 0.4691E-03 100 0.53617 -0.01928 13 17 0.6471E-03 9 17 0.8058E+01 0.3838E-03 110 0.53501 -0.01908 13 17 0.5882E-03 9 17 0.7495E+01 0.2923E-03 120 0.53398 -0.01891 13 17 0.5327E-03 9 17 0.6952E+01 0.2076E-03 130 0.53306 -0.01875 13 17 0.4825E-03 9 17 0.6444E+01 0.1338E-03 140 0.53225 -0.01862 13 17 0.4375E-03 9 17 0.5990E+01 0.6980E-04 150 0.53154 -0.01850 12 17 0.4054E-03 9 17 0.5586E+01 0.1395E-04 160 0.53091 -0.01839 12 17 0.3777E-03 9 17 0.5224E+01 0.3427E-04 170 0.53036 -0.01830 12 17 0.3524E-03 9 17 0.4897E+01 0.7653E-04 180 0.52988 -0.01822 12 17 0.3301E-03 9 17 0.4607E+01 0.1121E-03 190 0.52945 -0.01815 12 17 0.3099E-03 9 17 0.4345E+01 0.1430E-03 200 0.52908 -0.01809 38 16 0.3194E-03 9 17 0.4111E+01 0.1690E-03 210 0.52875 -0.01803 38 16 0.3417E-03 9 17 0.3902E+01 0.1915E-03 220 0.52847 -0.01798 38 16 0.3603E-03 9 17 0.3711E+01 0.2108E-03 230 0.52821 -0.01794 38 16 0.3765E-03 9 17 0.3542E+01 0.2272E-03 240 0.52799 -0.01790 38 16 0.3899E-03 9 17 0.3387E+01 0.2406E-03 250 0.52780 -0.01787 38 16 0.4010E-03 9 17 0.3252E+01 0.2528E-03 260 0.52763 -0.01784 38 16 0.4102E-03 9 17 0.3125E+01 0.2629E-03 270 0.52748 -0.01781 38 16 0.4186E-03 9 17 0.3012E+01 0.2716E-03 280 0.52735 -0.01779 38 16 0.4240E-03 9 17 0.2913E+01 0.2780E-03 290 0.52723 -0.01777 38 16 0.4289E-03 9 17 0.2822E+01 0.2840E-03 300 0.52713 -0.01775 38 16 0.4334E-03 9 17 0.2740E+01 0.2890E-03 310 0.52704 -0.01773 38 16 0.4370E-03 9 17 0.2666E+01 0.2933E-03 320 0.52697 -0.01772 38 16 0.4395E-03 9 17 0.2601E+01 0.2966E-03 330 0.52690 -0.01771 38 16 0.4415E-03 9 17 0.2543E+01 0.2996E-03 340 0.52684 -0.01770 38 16 0.4437E-03 9 17 0.2490E+01 0.3021E-03 350 0.52678 -0.01769 38 16 0.4449E-03 9 17 0.2443E+01 0.3042E-03 360 0.52674 -0.01768 38 16 0.4459E-03 9 17 0.2400E+01 0.3058E-03 370 0.52670 -0.01767 38 16 0.4461E-03 9 17 0.2354E+01 0.3070E-03 380 0.52666 -0.01766 38 16 0.4458E-03 9 17 0.2324E+01 0.3076E-03 390 0.52663 -0.01766 38 16 0.4480E-03 9 17 0.2291E+01 0.3088E-03 400 0.52660 -0.01765 38 16 0.4470E-03 9 17 0.2262E+01 0.3093E-03 410 0.52657 -0.01765 38 16 0.4474E-03 9 17 0.2238E+01 0.3099E-03 420 0.52655 -0.01764 38 16 0.4472E-03 9 17 0.2217E+01 0.3105E-03 430 0.52653 -0.01764 38 16 0.4473E-03 9 17 0.2199E+01 0.3110E-03 440 0.52652 -0.01764 38 16 0.4480E-03 9 17 0.2180E+01 0.3116E-03 450 0.52650 -0.01764 38 16 0.4475E-03 10 17 0.2177E+01 0.3115E-03 460 0.52649 -0.01763 38 16 0.4470E-03 10 17 0.2170E+01 0.3119E-03 470 0.52648 -0.01763 38 16 0.4474E-03 10 17 0.2166E+01 0.3119E-03 480 0.52647 -0.01763 38 16 0.4464E-03 10 17 0.2163E+01 0.3115E-03 490 0.52646 -0.01763 38 16 0.4464E-03 10 17 0.2157E+01 0.3123E-03 500 0.52645 -0.01763 38 16 0.4467E-03 10 17 0.2152E+01 0.3120E-03 510 0.52644 -0.01762 38 16 0.4454E-03 10 17 0.2147E+01 0.3113E-03 520 0.52644 -0.01762 38 16 0.4463E-03 10 17 0.2149E+01 0.3121E-03 530 0.52643 -0.01762 38 16 0.4450E-03 10 17 0.2144E+01 0.3116E-03 540 0.52643 -0.01762 38 16 0.4453E-03 10 17 0.2138E+01 0.3116E-03 550 0.52642 -0.01762 38 16 0.4450E-03 10 17 0.2137E+01 0.3117E-03 560 0.52642 -0.01762 38 16 0.4453E-03 10 17 0.2135E+01 0.3112E-03 570 0.52642 -0.01762 38 16 0.4448E-03 10 17 0.2133E+01 0.3117E-03 580 0.52641 -0.01762 38 16 0.4441E-03 10 17 0.2130E+01 0.3111E-03 590 0.52641 -0.01762 38 16 0.4448E-03 10 17 0.2131E+01 0.3112E-03 600 0.52641 -0.01762 38 16 0.4449E-03 10 17 0.2129E+01 0.3115E-03 610 0.52641 -0.01762 38 16 0.4438E-03 10 17 0.2128E+01 0.3113E-03 620 0.52640 -0.01762 38 16 0.4450E-03 10 17 0.2130E+01 0.3113E-03 630 0.52640 -0.01762 38 16 0.4446E-03 10 17 0.2132E+01 0.3119E-03 640 0.52640 -0.01762 38 16 0.4452E-03 10 17 0.2130E+01 0.3120E-03 650 0.52640 -0.01762 38 16 0.4453E-03 10 17 0.2129E+01 0.3119E-03 660 0.52640 -0.01762 38 16 0.4441E-03 10 17 0.2129E+01 0.3113E-03 670 0.52640 -0.01762 38 16 0.4444E-03 10 17 0.2129E+01 0.3115E-03 680 0.52640 -0.01762 38 16 0.4448E-03 10 17 0.2131E+01 0.3116E-03 690 0.52640 -0.01762 38 16 0.4447E-03 10 17 0.2130E+01 0.3122E-03 700 0.52640 -0.01762 38 16 0.4445E-03 10 17 0.2126E+01 0.3116E-03 710 0.52640 -0.01761 38 16 0.4442E-03 10 17 0.2124E+01 0.3114E-03 720 0.52640 -0.01761 38 16 0.4442E-03 10 17 0.2123E+01 0.3111E-03 730 0.52640 -0.01761 38 16 0.4438E-03 10 17 0.2122E+01 0.3111E-03 740 0.52640 -0.01761 38 16 0.4438E-03 10 17 0.2122E+01 0.3110E-03 750 0.52640 -0.01761 38 16 0.4442E-03 10 17 0.2123E+01 0.3113E-03 ****** ITERATION LIMIT REACHED ****** FORCE COEFFICIENTS, PRESSURE COEFFICIENT, AND MACH NUMBER (OR SIMILARITY PARAMETER) ON BODY AND DIVIDING STREAM LINE. MEDIUM MESH CL = 0.526396 CM = -0.017614 CP* = -0.603170 LOWER UPPER Y=0- Y=0+ I X CP M1 CP M1 1 -4.759090 -0.013205 0.756358 -0.013205 0.756358 B * 2 -1.154130 0.029694 0.735501 0.029694 0.735501 B * 3 -0.798421 0.066364 0.717192 0.066364 0.717192 B * 4 -0.473078 0.124216 0.687315 0.124216 0.687315 B * 5 -0.176356 0.285490 0.596174 0.285490 0.596174 B * 6 -0.074485 0.543367 0.410337 0.543367 0.410337 B * 7 -0.032465 0.814867 0.000000 0.814867 0.000000 B * 8 -0.010907 1.062881 0.000000 1.062881 0.000000 B * AIRFOIL LEADING EDGE AIRFOIL LEADING EDGE 9 0.002981 1.370034 0.000000 0.666150 0.281636 L U * 10 0.014039 0.470612 0.470265 -0.359349 0.907275 L U * 11 0.024707 0.155700 0.670496 -0.932535 1.113059 L * U 12 0.037083 -0.032508 0.765558 -1.221865 1.203645 L * U 13 0.054190 -0.166789 0.826727 -1.134010 1.176876 L * U 14 0.081200 -0.267676 0.869859 -1.147942 1.181161 L * U 15 0.122447 -0.335143 0.897547 -1.186646 1.192986 L * U 16 0.173324 -0.366933 0.910302 -1.223846 1.204242 L * U 17 0.225942 -0.370111 0.911567 -1.250687 1.212298 L * U 18 0.277060 -0.355773 0.905845 -1.267738 1.217388 L * U 19 0.326276 -0.332284 0.896391 -1.277280 1.220228 L * U 20 0.373966 -0.304442 0.885055 -1.280921 1.221309 L * U 21 0.420605 -0.274650 0.872762 -1.279359 1.220845 L * U 22 0.466597 -0.244141 0.859991 -1.272002 1.218658 L * U 23 0.512245 -0.213282 0.846877 -1.084281 1.161450 L * U 24 0.557751 -0.182392 0.833544 -0.466713 0.949223 L U * 25 0.603241 -0.151461 0.819976 -0.051320 0.774418 U L * 26 0.648791 -0.120178 0.806021 -0.076733 0.786230 UL * 27 0.694470 -0.087886 0.791358 -0.079071 0.787307 B * 28 0.740383 -0.053860 0.775607 -0.065128 0.780858 B * 29 0.786719 -0.016346 0.757863 -0.038450 0.768368 LU * 30 0.833793 0.026995 0.736831 0.001036 0.749499 LU * 31 0.882101 0.082102 0.709189 0.056624 0.722100 LU * 32 0.932402 0.162528 0.666793 0.142993 0.677335 B * 33 0.985879 0.327604 0.569980 0.318583 0.575691 B * AIRFOIL TRAILING EDGE AIRFOIL TRAILING EDGE 34 1.044481 0.302537 0.585713 0.302537 0.585713 B * 35 1.111798 0.196759 0.647907 0.196759 0.647907 B * 36 1.195818 0.137188 0.680436 0.137188 0.680436 B * 37 1.322245 0.087807 0.706265 0.087807 0.706265 B * 38 1.647911 0.049087 0.725875 0.049087 0.725875 B * 39 2.013718 0.029728 0.735484 0.029728 0.735484 B * 40 2.372788 0.015475 0.742479 0.015475 0.742479 B * 41 4.821552 -0.001483 0.750717 -0.001483 0.750717 B * Y(J) J= 1 TO 32 -5.200000 -1.722835 -1.021059 -0.715700 -0.542401 -0.429040 -0.347855 -0.285868 -0.236187 -0.194798 -0.159191 -0.127701 -0.099167 -0.072733 -0.047741 -0.023653 0.023653 0.047741 0.072733 0.099167 0.127701 0.159191 0.194798 0.236187 0.285868 0.347855 0.429040 0.542401 0.715700 1.021059 1.722835 5.200000 WE = 1.9500 EPS = 0.2000 MAXIT FOR THIS MESH = 1500 ITER CL CM IERR JERR ERROR IRL JRL BIGRL ERCIRC 10 0.52817 -0.02139 8 33 0.3370E-02 18 32 0.2693E+03 0.4199E-03 20 0.53041 -0.02232 57 61 0.1344E-02 17 32 0.1543E+03 0.5386E-03 30 0.53622 -0.02394 51 56 0.9470E-03 17 32 0.1007E+03 0.9151E-03 40 0.54025 -0.02382 47 43 0.7994E-03 17 32 0.6873E+02 0.5714E-03 50 0.54075 -0.02287 29 61 0.4075E-03 17 32 0.4551E+02 0.1222E-03 60 0.54005 -0.02205 19 61 0.3374E-03 17 32 0.2481E+02 0.8452E-04 70 0.54013 -0.02165 12 59 0.2605E-03 17 32 0.1637E+02 0.4584E-04 80 0.53970 -0.02138 45 32 0.1364E-03 17 32 0.1152E+02 0.1184E-03 90 0.53901 -0.02117 44 32 0.1042E-03 17 32 0.1131E+02 0.1129E-03 100 0.53832 -0.02101 38 32 0.8341E-04 17 32 0.1200E+02 0.1207E-03 110 0.53761 -0.02089 45 32 0.1074E-03 17 32 0.1286E+02 0.1092E-03 120 0.53706 -0.02084 44 32 0.9824E-04 17 32 0.1340E+02 0.8428E-04 130 0.53660 -0.02078 44 32 0.8628E-04 17 32 0.1348E+02 0.7361E-04 140 0.53620 -0.02074 43 32 0.7822E-04 17 32 0.1347E+02 0.6098E-04 150 0.53585 -0.02069 36 32 0.6613E-04 17 32 0.1297E+02 0.5805E-04 160 0.53549 -0.02062 44 32 0.6316E-04 17 32 0.1224E+02 0.5889E-04 170 0.53515 -0.02056 44 32 0.6038E-04 17 32 0.1143E+02 0.5645E-04 180 0.53481 -0.02049 44 32 0.5713E-04 17 32 0.1051E+02 0.5543E-04 190 0.53449 -0.02043 44 32 0.5520E-04 17 32 0.9658E+01 0.5269E-04 200 0.53418 -0.02037 44 32 0.5131E-04 17 32 0.8930E+01 0.4900E-04 210 0.53390 -0.02032 44 32 0.4805E-04 17 32 0.8310E+01 0.4637E-04 220 0.53363 -0.02027 44 32 0.4485E-04 17 32 0.7813E+01 0.4315E-04 230 0.53338 -0.02023 44 32 0.4203E-04 17 32 0.7306E+01 0.4053E-04 240 0.53314 -0.02019 44 32 0.3953E-04 17 32 0.6889E+01 0.3785E-04 250 0.53292 -0.02015 44 32 0.3693E-04 17 32 0.6414E+01 0.3552E-04 260 0.53272 -0.02012 44 32 0.3429E-04 17 32 0.6023E+01 0.3308E-04 270 0.53253 -0.02008 44 32 0.3227E-04 17 32 0.5607E+01 0.3111E-04 280 0.53235 -0.02005 44 32 0.3020E-04 17 32 0.5221E+01 0.2915E-04 290 0.53218 -0.02002 44 32 0.2805E-04 17 32 0.4896E+01 0.2724E-04 300 0.53202 -0.01999 44 32 0.2629E-04 17 32 0.4579E+01 0.2551E-04 310 0.53187 -0.01997 44 32 0.2447E-04 17 32 0.4272E+01 0.2414E-04 320 0.53174 -0.01995 44 32 0.2291E-04 17 32 0.4004E+01 0.2229E-04 330 0.53161 -0.01992 44 32 0.2149E-04 17 32 0.3748E+01 0.2068E-04 340 0.53149 -0.01990 44 32 0.1991E-04 17 32 0.3492E+01 0.1943E-04 350 0.53137 -0.01988 44 32 0.1874E-04 17 32 0.3270E+01 0.1836E-04 360 0.53127 -0.01987 45 32 0.1750E-04 17 32 0.3023E+01 0.1693E-04 370 0.53117 -0.01985 44 32 0.1637E-04 17 32 0.2827E+01 0.1591E-04 380 0.53108 -0.01983 44 31 0.1508E-04 17 32 0.2649E+01 0.1484E-04 390 0.53100 -0.01982 44 31 0.1422E-04 17 32 0.2475E+01 0.1371E-04 400 0.53092 -0.01980 44 32 0.1313E-04 17 32 0.2316E+01 0.1287E-04 410 0.53084 -0.01979 44 32 0.1240E-04 17 32 0.2170E+01 0.1210E-04 420 0.53077 -0.01978 44 32 0.1169E-04 17 32 0.2053E+01 0.1121E-04 430 0.53071 -0.01977 44 32 0.1078E-04 17 32 0.1892E+01 0.1019E-04 440 0.53065 -0.01976 44 32 0.1006E-04 17 32 0.1768E+01 0.9537E-05 450 0.53059 -0.01975 44 32 0.9385E-05 17 32 0.1640E+01 0.9239E-05 ........SOLUTION CONVERGED........ PRINTOUT IN PHYSICAL VARIABLES. DEFINITION OF SIMILARITY PARAMETERS BY KRUPP BOUNDARY CONDITION FOR FREE AIR DIFFERENCE EQUATIONS ARE FULLY CONSERVATIVE. KUTTA CONDITION IS ENFORCED. MACH = 0.7500000 DELTA = 0.1200000 ALPHA = 2.0000000 K = 2.3977063 DOUBLET STRENGTH = 0.6842346 PARAMETERS USED TO TRANSFORM VARIABLES TO TRANSONIC SCALING CPFACT = 0.3018734 CDFACT = 0.0362248 CMFACT = 0.3018734 CLFACT = 0.3018734 YFACT = 2.3410406 VFACT = 6.8754935 FORCE COEFFICIENTS, PRESSURE COEFFICIENT, AND MACH NUMBER (OR SIMILARITY PARAMETER) ON BODY AND DIVIDING STREAM LINE. FINAL MESH CL = 0.530591 CM = -0.019749 CP* = -0.603170 LOWER UPPER Y=0- Y=0+ I X CP M1 CP M1 1 -4.759090 -0.004919 0.752375 -0.004919 0.752375 B * 2 -1.451373 0.016644 0.741908 0.016644 0.741908 B * 3 -1.154130 0.031138 0.734789 0.031138 0.734789 B * 4 -0.959227 0.039341 0.730729 0.039341 0.730729 B * 5 -0.798421 0.050024 0.725407 0.050024 0.725407 B * 6 -0.644242 0.066479 0.717134 0.066479 0.717134 B * 7 -0.473078 0.097293 0.701377 0.097293 0.701377 B * 8 -0.290925 0.157576 0.669481 0.157576 0.669481 B * 9 -0.176356 0.250392 0.617156 0.250392 0.617156 B * 10 -0.113082 0.362603 0.547258 0.362603 0.547258 B * 11 -0.074485 0.486806 0.457605 0.486806 0.457605 B * 12 -0.049489 0.622216 0.333445 0.622216 0.333445 B * 13 -0.032465 0.767556 0.075925 0.767556 0.075925 B * 14 -0.020228 0.922323 0.000000 0.922323 0.000000 B * 15 -0.010907 1.087430 0.000000 1.087430 0.000000 B * 16 -0.003416 1.266029 0.000000 1.266029 0.000000 B * AIRFOIL LEADING EDGE AIRFOIL LEADING EDGE 17 0.002981 1.837557 0.000000 0.872999 0.000000 L U * 18 0.008679 1.046172 0.000000 -0.035940 0.767182 L U * 19 0.014039 0.675354 0.269523 -0.427078 0.933956 L U * 20 0.019292 0.449739 0.486095 -0.635343 1.011601 L * 21 0.024707 0.295623 0.589978 -0.814665 1.073967 L * U 22 0.030523 0.181314 0.656496 -0.911830 1.106292 L * U 23 0.037083 0.090487 0.704888 -0.917512 1.108153 L * U 24 0.044772 0.013855 0.743270 -0.953268 1.119794 L * U 25 0.054190 -0.054174 0.775754 -0.993476 1.132741 L * U 26 0.066066 -0.116450 0.804342 -1.029814 1.144316 L * U 27 0.081200 -0.173420 0.829631 -1.064529 1.155266 L * U 28 0.100083 -0.223487 0.851236 -1.097753 1.165649 L * U 29 0.122447 -0.264321 0.868459 -1.128524 1.175184 L * U 30 0.147263 -0.294535 0.880986 -1.155673 1.183533 L * U 31 0.173324 -0.314399 0.889126 -1.178757 1.190585 L * U 32 0.199723 -0.325391 0.893598 -1.197972 1.196424 L * U 33 0.225942 -0.329377 0.895214 -1.213780 1.201206 L * U 34 0.251747 -0.328086 0.894691 -1.226685 1.205096 L * U 35 0.277060 -0.322925 0.892597 -1.237141 1.208239 L * U 36 0.301889 -0.314969 0.889358 -1.245530 1.210754 L * U 37 0.326276 -0.305008 0.885287 -1.252153 1.212737 L * U 38 0.350282 -0.293610 0.880605 -1.257238 1.214256 L * U 39 0.373966 -0.281189 0.875475 -1.260956 1.215366 L * U 40 0.397389 -0.268040 0.870011 -1.263432 1.216105 L * U 41 0.420605 -0.254372 0.864294 -1.264753 1.216499 L * U 42 0.443660 -0.240337 0.858385 -1.264974 1.216565 L * U 43 0.466597 -0.226036 0.852322 -1.264116 1.216309 L * U 44 0.489449 -0.211547 0.846134 -1.262154 1.215724 L * U 45 0.512245 -0.196914 0.839838 -1.258755 1.214709 L * U 46 0.535006 -0.182157 0.833441 -0.938870 1.115121 L * U 47 0.557751 -0.167290 0.826947 -0.313260 0.888661 L U * 48 0.580493 -0.152309 0.820350 -0.021770 0.760454 U L * 49 0.603241 -0.137191 0.813639 -0.048456 0.773076 UL * 50 0.626005 -0.121901 0.806795 -0.064782 0.780697 UL * 51 0.648791 -0.106384 0.799790 -0.073474 0.784725 UL * 52 0.671609 -0.090569 0.792586 -0.076164 0.785967 B * 53 0.694470 -0.074358 0.785133 -0.073988 0.784962 B * 54 0.717388 -0.057617 0.777362 -0.067739 0.782070 B * 55 0.740383 -0.040186 0.769187 -0.057963 0.777524 B * 56 0.763482 -0.021840 0.760488 -0.044990 0.771449 LU * 57 0.786719 -0.002288 0.751106 -0.028943 0.763868 B * 58 0.810138 0.018865 0.740822 -0.009738 0.754694 B * 59 0.833793 0.042199 0.729309 0.012962 0.743706 LU * 60 0.857753 0.068556 0.716082 0.039842 0.730480 B * 61 0.882101 0.099270 0.700354 0.072158 0.714256 LU * 62 0.906941 0.136698 0.680697 0.112266 0.693592 B * 63 0.932402 0.185670 0.654085 0.165130 0.665376 B * 64 0.958646 0.259028 0.612060 0.244073 0.620858 B * 65 0.985879 0.408999 0.515596 0.403223 0.519643 B * AIRFOIL TRAILING EDGE AIRFOIL TRAILING EDGE 66 1.014370 0.376650 0.537868 0.376650 0.537868 B * 67 1.044481 0.274976 0.602536 0.274976 0.602536 B * 68 1.076713 0.219538 0.635029 0.219538 0.635029 B * 69 1.111798 0.182138 0.656041 0.182138 0.656041 B * 70 1.150867 0.153703 0.671576 0.153703 0.671576 B * 71 1.195818 0.130265 0.684116 0.130265 0.684116 B * 72 1.250238 0.109495 0.695039 0.109495 0.695039 B * 73 1.322245 0.089266 0.705516 0.089266 0.705516 B * 74 1.436261 0.067593 0.716570 0.067593 0.716570 B * 75 1.647911 0.048405 0.726216 0.048405 0.726216 B * 76 1.849817 0.036374 0.732200 0.036374 0.732200 B * 77 2.013718 0.029455 0.735619 0.029455 0.735619 B * 78 2.177861 0.024665 0.737977 0.024665 0.737977 B * 79 2.372788 0.020578 0.739983 0.020578 0.739983 B * 80 2.664829 0.013094 0.743642 0.013094 0.743642 B * 81 4.821552 0.002074 0.748996 0.002074 0.748996 B * Y(J) J= 1 TO 64 -5.200000 -2.594099 -1.722835 -1.285221 -1.021059 -0.843610 -0.715700 -0.618740 -0.542401 -0.480483 -0.429040 -0.385438 -0.347855 -0.314984 -0.285868 -0.259787 -0.236187 -0.214639 -0.194798 -0.176391 -0.159191 -0.143013 -0.127701 -0.113124 -0.099167 -0.085732 -0.072733 -0.060093 -0.047741 -0.035615 -0.023653 -0.011800 0.011800 0.023653 0.035615 0.047741 0.060093 0.072733 0.085732 0.099167 0.113124 0.127701 0.143013 0.159191 0.176391 0.194798 0.214639 0.236187 0.259787 0.285868 0.314984 0.347855 0.385438 0.429040 0.480483 0.542401 0.618740 0.715700 0.843610 1.021059 1.285221 1.722835 2.594099 5.200000 FLOW AT EACH GRID POINT. P PARABOLIC H HYPERBOLIC S SHOCK - ELLIPTIC 64 ------------------------------------------------------------------------------- 63 ------------------------------------------------------------------------------- 62 ------------------------------------------------------------------------------- 61 ------------------------------------------------------------------------------- 60 ------------------------------------------------------------------------------- 59 ------------------------------------------------------------------------------- 58 ------------------------------------------------------------------------------- 57 -------------------------------------PHHS-------------------------------------- 56 ----------------------------------PHHHHHHHS------------------------------------ 55 ---------------------------------PHHHHHHHHHS----------------------------------- 54 --------------------------------PHHHHHHHHHHS----------------------------------- 53 -------------------------------PHHHHHHHHHHHS----------------------------------- 52 ------------------------------PHHHHHHHHHHHHHS---------------------------------- 51 ------------------------------PHHHHHHHHHHHHHS---------------------------------- 50 -----------------------------PHHHHHHHHHHHHHHS---------------------------------- 49 -----------------------------PHHHHHHHHHHHHHHS---------------------------------- 48 ----------------------------PHHHHHHHHHHHHHHHS---------------------------------- 47 ----------------------------PHHHHHHHHHHHHHHHS---------------------------------- 46 ----------------------------PHHHHHHHHHHHHHHHS---------------------------------- 45 ---------------------------PHHHHHHHHHHHHHHHHHS--------------------------------- 44 ---------------------------PHHHHHHHHHHHHHHHHHS--------------------------------- 43 ---------------------------PHHHHHHHHHHHHHHHHHS--------------------------------- 42 --------------------------PHHHHHHHHHHHHHHHHHHS--------------------------------- 41 --------------------------PHHHHHHHHHHHHHHHHHHS--------------------------------- 40 --------------------------PHHHHHHHHHHHHHHHHHHS--------------------------------- 39 -------------------------PHHHHHHHHHHHHHHHHHHHS--------------------------------- 38 -------------------------PHHHHHHHHHHHHHHHHHHHS--------------------------------- 37 ------------------------PHHHHHHHHHHHHHHHHHHHHS--------------------------------- 36 -----------------------PHHHHHHHHHHHHHHHHHHHHHS--------------------------------- 35 -----------------------PHHHHHHHHHHHHHHHHHHHHHS--------------------------------- 34 ---------------------PHHHHHHHHHHHHHHHHHHHHHHHS--------------------------------- 33 --------------------PHHHHHHHHHHHHHHHHHHHHHHHHS--------------------------------- 32 ------------------------------------------------------------------------------- 31 ------------------------------------------------------------------------------- 30 ------------------------------------------------------------------------------- 29 ------------------------------------------------------------------------------- 28 ------------------------------------------------------------------------------- 27 ------------------------------------------------------------------------------- 26 ------------------------------------------------------------------------------- 25 ------------------------------------------------------------------------------- 24 ------------------------------------------------------------------------------- 23 ------------------------------------------------------------------------------- 22 ------------------------------------------------------------------------------- 21 ------------------------------------------------------------------------------- 20 ------------------------------------------------------------------------------- 19 ------------------------------------------------------------------------------- 18 ------------------------------------------------------------------------------- 17 ------------------------------------------------------------------------------- 16 ------------------------------------------------------------------------------- 15 ------------------------------------------------------------------------------- 14 ------------------------------------------------------------------------------- 13 ------------------------------------------------------------------------------- 12 ------------------------------------------------------------------------------- 11 ------------------------------------------------------------------------------- 10 ------------------------------------------------------------------------------- 9 ------------------------------------------------------------------------------- 8 ------------------------------------------------------------------------------- 7 ------------------------------------------------------------------------------- 6 ------------------------------------------------------------------------------- 5 ------------------------------------------------------------------------------- 4 ------------------------------------------------------------------------------- 3 ------------------------------------------------------------------------------- 2 ------------------------------------------------------------------------------- 1 ------------------------------------------------------------------------------- MACH NO. MAP. ROUNDED TO NEAREST .1 88888888888888888888888888888888888888888888888888888888888888888888888888888888 88888888888888888888888888888888888888888888888888888888888888888888888888888888 88888888888888888888888888888888888888888888888888888888888888888888888888888887 88888888888888888888888888888888888888888888888888888888888888888888888888888887 88888888888888888888888888889999999999999999988888888888888888888888888888877777 78888888888888888888888888999999999999999999999888888888888888888888888877777777 77778888888888888888888899999999999******999999988888888888888888888887777777777 77777888888888888888888899999999**********99999988888888888888888887777777777777 7777778888888888888888899999999************9999888888888888888888777777777777777 777777888888888888888889999999*******11111*9999888888888888888877777777777777777 777777788888888888888889999999*****11111111*998888888888888887777777777777777777 77777777888888888888888999999*****111111111*998888888888888877777777777777777777 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77777777777777777777777777777777777777777777777777777777777777777777777777777777 77777777777777777777777777777777777777777777777777777777777777777777777777777777 77777777777777777777777777777777777777777777777777777777777777777777777777777777 L T PRINTER PLOT OF CP ON BODY AND DIVIDING STREAMLINE U FOR CP(UPPER) L FOR CP(LOWER) B FOR CP(UPPER)=CP(LOWER) --- FOR CP SONIC UUUUUUUUUU UUU U UU UU U U U U - - - - - - - - ---U--------------------------------- -- - - - - - - - - U LLL LL LLL U L LLL L LL L LLL L UUBBBU U U LLB B B B B B L LBU B B B B B B B L LB B B B B LU B B L L BB B B B L B B L B B B L B U B L B B L SONIC LINE COORDINATES Y XSONIC 0.61874 0.35968 0.44087 0.54240 0.29895 0.47611 0.48048 0.26304 0.49306 0.42904 0.23595 0.50342 0.38544 0.21447 0.51074 0.34785 0.19639 0.51721 0.31498 0.18146 0.52199 0.28587 0.16801 0.52567 0.25979 0.15643 0.52860 0.23619 0.14537 0.53100 0.21464 0.13617 0.53304 0.19480 0.12700 0.53491 0.17639 0.11852 0.53678 0.15919 0.11095 0.53841 0.14301 0.10306 0.53982 0.12770 0.09587 0.54106 0.11312 0.08909 0.54213 0.09917 0.08159 0.54307 0.08573 0.07524 0.54389 0.07273 0.06810 0.54462 0.06009 0.06120 0.54524 0.04774 0.05347 0.54578 0.03561 0.04557 0.54624 0.02365 0.03661 0.54662 0.01180 0.02561 0.54692 BODY LOCATION SONIC LINE PLOT Y VS X * FOR SONIC POINTS + + + + + + + + + + + ....................................................................................................... 1.5 + . . + . . . . . . . . . . . . . . . . . . 1.0 + . . + . . . . . . . . . . . . . . . * * . . * * . 0.5 + . * * . + . * * . . * * . . * * . . * * . . * * . . * * . . * * . . ** * . . ** * . 0.0 + . *--------------BODY S*IT--------------- . + . . . . . . . . . . . . . . . . . . -0.5 + . . + . . . . . . . . . . . . . . . . . . -1.0 + . . + ....................................................................................................... + + + + + + + + + + + -0.75 -0.50 -0.25 0.00 0.25 0.50 0.75 1.00 1.25 1.50 1.75 ( 50 PTS) INVISCID WAKE PROFILES FOR INDIVIDUAL SHOCK WAVES WITHIN MOMENTUM CONTOUR SHOCK 1 WAVE DRAG FOR THIS SHOCK= 0.013055 Y CD(Y) PO/POINF 0.00000000 0.05323364 0.96532238 0.01179969 0.05270910 0.96566403 0.02365306 0.05218565 0.96600503 0.03561476 0.05143723 0.96649259 0.04774144 0.05049252 0.96710801 0.06009285 0.04936729 0.96784097 0.07273307 0.04806654 0.96868831 0.08573192 0.04658599 0.96965277 0.09916656 0.04491172 0.97074348 0.11312358 0.04302011 0.97197568 0.12770136 0.04087633 0.97337222 0.14301318 0.03843323 0.97496367 0.15919104 0.03563136 0.97678888 0.17639072 0.03240333 0.97889173 0.19479822 0.03012371 0.98037672 0.21463855 0.02893322 0.98115224 0.23618728 0.02690643 0.98247254 0.25978664 0.02419216 0.98424065 0.28586808 0.02087746 0.98639995 0.31498396 0.01701372 0.98891687 0.34785455 0.01267933 0.99174041 0.38543820 0.00804893 0.99475676 0.42903957 0.00584013 0.99619561 0.48048288 0.00316313 0.99793947 0.54240072 0.00108592 0.99929261 0.61873996 0.00003114 0.99997973 CALCULATION OF DRAG COEFFICIENT BY MOMENTUM INTEGRAL METHOD BOUNDARIES OF CONTOUR USED CONTRIBUTION TO CD UPSTREAM X = -0.176356 CDUP = -0.001201 DOWNSTREAM X = 1.322245 CDDOWN = 0.000993 TOP Y = 2.594099 CDTOP = 0.000337 BOTTOM Y = -2.594099 CDBOT = 0.000050 TOTAL CONTRIBUTIONS AROUND CONTOUR = 0.000179 THERE ARE 1 SHOCKS INSIDE CONTOUR. TOTAL CDWAVE = 0.013055 NOTE - ALL SHOCKS CONTAINED WITHIN CONTOUR CDWAVE EQUALS TOTAL WAVE DRAG DRAG CALCULATED FROM MOMENTUM INTEGRAL CD = 0.013234 STOP