********************************************************************* * * * PROGRAM TSFOIL * * SOLVES * * INVISCID FLOW PAST THIN TWO DIMENSIONAL LIFTINGAIRFOIL, * * 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 n2412.tsd TEST OF DATA POINT INPUT CASE , NACA2412 EMACH = 0.75000 POR = 0.00000 IMIN = 1 BCTYPE = 1 AMESH = F DELTA = 0.12000 CLSET = 0.00000 IMAXI = 77 BCFOIL = 3 PHYS = T ALPHA = 0.00000 EPS = 0.20000 JMIN = 1 PSTART = 1 PSAVE = F AK = 0.00000 RIGF = 0.00000 JMAXI = 56 PRTFLO = 1 KUTTA = T GAM = 1.40000 WCIRC = 1.00000 MAXIT = 1500 IPRTER = 10 FCR = T F = 0.00000 CVERGE = 0.00001 NU = 21 SIMDEF = 3 H = 0.00000 DVERGE = 10.0 NL = 26 ICUT = 2 WE = 1.80,1.90,1.95 XIN -1.075000 -0.950000 -0.825000 -0.700000 -0.575000 -0.450000 -0.350000 -0.250000 -0.175000 -0.125000 -0.075000 -0.052500 -0.035000 -0.022500 -0.015000 -0.007500 -0.002500 0.002500 0.007500 0.012500 0.017500 0.022500 0.027500 0.032500 0.037500 0.045000 0.055000 0.065000 0.075000 0.085000 0.097500 0.115000 0.140625 0.171875 0.203125 0.234375 0.265625 0.296875 0.328125 0.359375 0.390625 0.421875 0.453125 0.484375 0.515625 0.546875 0.578125 0.609375 0.640625 0.671875 0.703125 0.734375 0.765625 0.796875 0.828125 0.859375 0.885000 0.900000 0.915000 0.930000 0.945000 0.960000 0.975000 0.990000 1.000000 1.010000 1.025000 1.050000 1.090000 1.150000 1.225000 1.300000 1.400000 1.500000 1.625000 1.750000 1.875000 YIN -5.200000 -4.400000 -3.600000 -3.000000 -2.400000 -1.950000 -1.600000 -1.350000 -1.150000 -0.950000 -0.800000 -0.650000 -0.550000 -0.450000 -0.390000 -0.340000 -0.300000 -0.270000 -0.240000 -0.210000 -0.180000 -0.150000 -0.125000 -0.100000 -0.075000 -0.050000 -0.030000 -0.010000 0.010000 0.030000 0.050000 0.075000 0.100000 0.125000 0.150000 0.180000 0.210000 0.240000 0.270000 0.300000 0.340000 0.390000 0.450000 0.550000 0.650000 0.800000 0.950000 1.150000 1.350000 1.600000 1.950000 2.400000 3.000000 3.600000 4.400000 5.200000 XU 0.000000 0.047380 0.097300 0.147450 0.197720 0.248050 0.298420 0.348820 0.399230 0.449630 0.500000 0.550320 0.600590 0.650780 0.700900 0.750940 0.800890 0.850760 0.900550 0.950270 1.000000 YU 0.000000 0.034300 0.048960 0.059590 0.067600 0.073630 0.077860 0.080370 0.081230 0.079880 0.076860 0.072460 0.066900 0.060330 0.052930 0.044830 0.036190 0.027220 0.018180 0.009190 0.000000 XL 0.000000 0.006620 0.009310 0.014550 0.027360 0.052620 0.077710 0.102700 0.152550 0.202280 0.251950 0.301580 0.351180 0.400770 0.450370 0.500000 0.549680 0.599410 0.649220 0.699100 0.749060 0.799110 0.849240 0.899450 0.949730 1.000000 YL 0.000000 -0.008640 -0.010250 -0.012620 -0.016490 -0.021660 -0.025350 -0.028280 -0.032670 -0.035760 -0.037830 -0.038980 -0.039170 -0.038390 -0.036080 -0.032740 -0.028660 -0.024060 -0.019130 -0.014050 -0.009030 -0.004350 -0.000380 0.002500 0.003450 0.000000 SCALED POR= 0.00000 AIRFOIL GEOMETRY INFORMATION PRINTOUT IN PHYSICAL VARIABLES NORMALIZED BY CHORD LENGTH MAX THICKNESS = 0.11989882 AIRFOIL VOLUME= 0.07571617 MAX CAMBER = 0.02205276 UPPER SURFACE LOWER SURFACE X Y DY/DX Y DY/DX THICKNESS CAMBER 0.00250000 0.00183303 0.74197441 -0.00353205 -1.45516241 0.00268254 -0.00084951 0.00750000 0.00561502 0.76875150 -0.00928980 -0.64311969 0.00745241 -0.00183739 0.01250000 0.00949987 0.78312421 -0.01173540 -0.44973469 0.01061764 -0.00111776 0.01750000 0.01342558 0.78509235 -0.01373306 -0.34684211 0.01357932 -0.00015374 0.02250000 0.01733012 0.77465612 -0.01526352 -0.27219024 0.01629682 0.00103330 0.02750000 0.02115147 0.75181532 -0.01652343 -0.23860595 0.01883745 0.00231402 0.03250000 0.02482760 0.71657008 -0.01768134 -0.22461271 0.02125447 0.00357313 0.03750000 0.02829650 0.66892028 -0.01877014 -0.21096724 0.02353332 0.00476318 0.04500000 0.03297559 0.57418728 -0.02027760 -0.19115125 0.02662659 0.00634900 0.05500000 0.03797279 0.42911124 -0.02206203 -0.16608091 0.03001742 0.00795538 0.06500000 0.04167354 0.31691954 -0.02361610 -0.14575170 0.03264482 0.00902872 0.07500000 0.04442882 0.24001688 -0.02499744 -0.13153411 0.03471313 0.00971569 0.08500000 0.04659151 0.19840330 -0.02626345 -0.12190379 0.03642748 0.01016403 0.09750000 0.04899916 0.19600296 -0.02771635 -0.11065662 0.03835776 0.01064141 0.11500000 0.05265545 0.21791466 -0.02952329 -0.09620866 0.04108937 0.01156608 0.14062500 0.05821194 0.20730579 -0.03176134 -0.07933356 0.04498664 0.01322530 0.17187500 0.06386830 0.15722102 -0.03400021 -0.06448025 0.04893425 0.01493404 0.20312500 0.06832064 0.13191542 -0.03580331 -0.05107810 0.05206198 0.01625866 0.23437500 0.07215623 0.11270329 -0.03720437 -0.03880265 0.05468030 0.01747593 0.26562500 0.07531715 0.08940155 -0.03824058 -0.02754115 0.05677887 0.01853829 0.29687500 0.07775727 0.06702814 -0.03891292 -0.01524371 0.05833509 0.01942217 0.32812500 0.07952797 0.04675075 -0.03919093 -0.00293796 0.05935945 0.02016852 0.35937500 0.08070525 0.02852559 -0.03912225 0.00724344 0.05991375 0.02079150 0.39062500 0.08123346 0.00375431 -0.03866535 0.02356442 0.05994941 0.02128405 0.42187500 0.08087910 -0.02559441 -0.03757968 0.04528676 0.05922939 0.02164971 0.45312500 0.07971802 -0.04737989 -0.03591653 0.05982499 0.05781727 0.02190074 0.48437500 0.07795253 -0.06550134 -0.03387903 0.07041297 0.05591578 0.02203675 0.51562500 0.07563207 -0.08277368 -0.03152654 0.07989516 0.05357930 0.02205276 0.54687500 0.07280059 -0.09808242 -0.02890617 0.08746850 0.05085338 0.02194721 0.57812500 0.06951892 -0.11182295 -0.02607875 0.09324048 0.04779884 0.02172009 0.60937500 0.06581888 -0.12483311 -0.02309383 0.09755430 0.04445636 0.02136252 0.64062500 0.06173259 -0.13640577 -0.01999606 0.10047398 0.04086433 0.02086826 0.67187500 0.05730967 -0.14650041 -0.01682894 0.10196483 0.03706931 0.02024037 0.70312500 0.05258401 -0.15581998 -0.01363973 0.10187571 0.03311187 0.01947214 0.73437500 0.04758161 -0.16412854 -0.01048294 0.09978163 0.02903228 0.01854934 0.76562500 0.04233901 -0.17116423 -0.00742715 0.09538898 0.02488308 0.01745593 0.79687500 0.03690039 -0.17663763 -0.00454717 0.08851103 0.02072378 0.01617661 0.82812500 0.03131783 -0.18029195 -0.00193093 0.07813286 0.01662438 0.01469345 0.85937500 0.02565452 -0.18180570 0.00028771 0.06343249 0.01268341 0.01297112 0.88499999 0.02099662 -0.18151152 0.00177147 0.05284843 0.00961257 0.01138405 0.89999998 0.01827939 -0.18070897 0.00252643 0.04796681 0.00787648 0.01040291 0.91500002 0.01557433 -0.18013480 0.00318042 0.03728904 0.00619695 0.00937738 0.93000001 0.01287019 -0.18058962 0.00358681 0.01495216 0.00464169 0.00822849 0.94499999 0.01015150 -0.18207438 0.00357069 -0.01904385 0.00329040 0.00686109 0.95999998 0.00740424 -0.18414763 0.00298217 -0.05740263 0.00221103 0.00519321 0.97500002 0.00463218 -0.18528190 0.00194352 -0.07783838 0.00134433 0.00328785 0.99000001 0.00185112 -0.18534768 0.00074437 -0.07880323 0.00055337 0.00129775 1.00000000 0.00000000 -0.18479790 0.00000000 -0.06862938 0.00000000 0.00000000 WE = 1.8000 EPS = 0.2000 MAXIT FOR THIS MESH = 375 ITERATION CL CM IERR JERR ERROR IRL JRL BIGRL ERCIRC 10 0.50812 -0.16829 12 7 0.5191E-01 6 8 0.1258E+03 0.5300E-01 20 0.59711 -0.15356 5 4 0.1715E-01 6 7 0.1889E+03 0.9031E-02 30 0.65544 -0.16194 12 7 0.9669E-02 6 7 0.9678E+02 0.9109E-02 40 0.71045 -0.17601 12 7 0.7322E-02 6 8 0.5859E+02 0.7674E-02 50 0.74226 -0.18318 12 7 0.4541E-02 6 7 0.4143E+02 0.4635E-02 60 0.76832 -0.19039 12 7 0.3645E-02 6 7 0.2834E+02 0.4039E-02 70 0.78895 -0.19593 12 7 0.2794E-02 6 7 0.2150E+02 0.3119E-02 80 0.80520 -0.20032 12 7 0.2190E-02 6 7 0.1656E+02 0.2480E-02 90 0.81792 -0.20342 12 7 0.1703E-02 6 7 0.1294E+02 0.1881E-02 100 0.82706 -0.20533 12 7 0.1245E-02 6 7 0.9975E+01 0.1342E-02 110 0.83372 -0.20668 12 7 0.9190E-03 6 7 0.7435E+01 0.9917E-03 120 0.83858 -0.20767 12 7 0.6689E-03 6 7 0.5543E+01 0.7006E-03 130 0.84215 -0.20842 12 7 0.4976E-03 6 7 0.4087E+01 0.5404E-03 140 0.84490 -0.20900 12 7 0.3782E-03 6 7 0.3049E+01 0.4114E-03 150 0.84698 -0.20944 12 7 0.2864E-03 6 7 0.2309E+01 0.3127E-03 160 0.84856 -0.20977 12 7 0.2178E-03 6 7 0.1751E+01 0.2381E-03 170 0.84977 -0.21002 12 7 0.1660E-03 6 7 0.1332E+01 0.1813E-03 180 0.85070 -0.21022 12 7 0.1266E-03 6 7 0.1016E+01 0.1390E-03 190 0.85140 -0.21036 12 7 0.9673E-04 6 7 0.7758E+00 0.1063E-03 200 0.85194 -0.21047 12 7 0.7393E-04 6 7 0.5922E+00 0.8130E-04 210 0.85236 -0.21056 12 7 0.5684E-04 6 7 0.4536E+00 0.6235E-04 220 0.85268 -0.21062 12 7 0.4338E-04 6 7 0.3481E+00 0.4804E-04 230 0.85292 -0.21067 12 7 0.3324E-04 6 7 0.2666E+00 0.3672E-04 240 0.85311 -0.21071 12 7 0.2554E-04 6 7 0.2037E+00 0.2849E-04 250 0.85325 -0.21074 12 7 0.1943E-04 6 7 0.1571E+00 0.2170E-04 260 0.85336 -0.21076 12 7 0.1512E-04 6 7 0.1204E+00 0.1645E-04 270 0.85345 -0.21078 12 7 0.1168E-04 6 7 0.9168E-01 0.1264E-04 280 0.85351 -0.21079 12 7 0.8847E-05 6 7 0.7085E-01 0.9894E-05 ........SOLUTION CONVERGED........ FORCE COEFFICIENTS, PRESSURE COEFFICIENT, AND MACH NUMBER (OR SIMILARITY PARAMETER) ON BODY AND DIVIDING STREAM LINE. COARSE MESH CL = 0.853511 CM = -0.210794 CP* = -0.603170 LOWER UPPER Y=0- Y=0+ I X CP M1 CP M1 1 -1.075000 0.029884 0.735407 0.029884 0.735407 B * 2 -0.575000 0.082275 0.709100 0.082275 0.709100 B * 3 -0.175000 0.187404 0.653123 0.187404 0.653123 B * 4 -0.035000 0.342818 0.560216 0.342818 0.560216 B * 5 -0.002500 0.450391 0.485609 0.450391 0.485609 B * AIRFOIL LEADING EDGE AIRFOIL LEADING EDGE 6 0.017500 0.518519 0.431740 0.594196 0.362642 U L * 7 0.037500 0.310628 0.580681 0.025490 0.737571 L U * 8 0.075000 0.137508 0.680265 -0.332205 0.896359 L U * 9 0.140625 -0.005433 0.752622 -0.691826 1.031652 L * U 10 0.265625 -0.099096 0.796478 -1.081921 1.160713 L * U 11 0.390625 -0.118175 0.805119 -1.195055 1.195539 L * U 12 0.515625 -0.030670 0.764687 -1.324625 1.234219 L * U 13 0.640625 0.126005 0.686370 -1.289800 1.223943 L * U 14 0.765625 0.287315 0.595064 -0.575341 0.989856 L * 15 0.885000 0.414646 0.511608 0.090690 0.704783 L U * 16 0.945000 0.447462 0.487792 0.156361 0.670138 L U * 17 1.000000 0.379001 0.536281 0.262128 0.610221 L U * AIRFOIL TRAILING EDGE AIRFOIL TRAILING EDGE 18 1.090000 0.206858 0.642230 0.206858 0.642230 B * 19 1.400000 0.111399 0.694045 0.111399 0.694045 B * 20 1.875000 0.048794 0.726022 0.048794 0.726022 B * Y(J) J= 1 TO 14 -5.20000 -2.40000 -1.15000 -0.550000 -0.300000 -0.180000 -0.750000E-01 0.750000E-01 0.180000 0.300000 0.550000 1.15000 2.40000 5.20000 WE = 1.9000 EPS = 0.2000 MAXIT FOR THIS MESH = 750 ITERATION CL CM IERR JERR ERROR IRL JRL BIGRL ERCIRC 10 0.85293 -0.21988 17 15 0.1642E-01 11 15 0.8241E+02 0.4022E-03 20 0.86383 -0.22586 15 15 0.1429E-01 11 15 0.1479E+03 0.6311E-02 30 0.87420 -0.22779 16 15 0.9716E-02 11 15 0.1513E+03 0.4365E-02 40 0.87953 -0.23028 15 15 0.1347E-01 11 15 0.1642E+03 0.4345E-02 50 0.88408 -0.23026 16 15 0.1037E-01 11 15 0.1595E+03 0.3293E-02 60 0.88769 -0.23293 15 15 0.1338E-01 11 15 0.1630E+03 0.4064E-02 70 0.89123 -0.23266 15 15 0.1080E-01 11 15 0.1540E+03 0.3664E-02 80 0.89408 -0.23534 15 15 0.1362E-01 11 15 0.1563E+03 0.4297E-02 90 0.89694 -0.23477 15 15 0.1106E-01 11 15 0.1485E+03 0.4146E-02 100 0.89909 -0.23755 16 15 0.1425E-01 11 15 0.1511E+03 0.4990E-02 110 0.90116 -0.23662 15 15 0.1087E-01 11 15 0.1405E+03 0.4556E-02 120 0.90310 -0.23928 16 15 0.1567E-01 11 15 0.1438E+03 0.5921E-02 130 0.90500 -0.23816 16 15 0.1122E-01 11 15 0.1340E+03 0.4821E-02 140 0.90681 -0.24065 16 15 0.1627E-01 11 15 0.1392E+03 0.6312E-02 150 0.90834 -0.23934 16 15 0.1141E-01 11 15 0.1312E+03 0.4905E-02 160 0.90978 -0.24171 16 15 0.1659E-01 11 15 0.1367E+03 0.6532E-02 170 0.91099 -0.24036 16 15 0.1158E-01 11 15 0.1292E+03 0.5007E-02 180 0.91222 -0.24259 16 15 0.1685E-01 11 15 0.1345E+03 0.6745E-02 190 0.91321 -0.24121 16 15 0.1173E-01 11 15 0.1276E+03 0.5090E-02 200 0.91427 -0.24333 16 15 0.1705E-01 11 15 0.1327E+03 0.6909E-02 210 0.91508 -0.24191 16 15 0.1184E-01 11 15 0.1262E+03 0.5155E-02 220 0.91599 -0.24395 16 15 0.1723E-01 11 15 0.1313E+03 0.7048E-02 230 0.91665 -0.24249 16 15 0.1192E-01 11 15 0.1250E+03 0.5223E-02 240 0.91743 -0.24449 16 15 0.1739E-01 11 15 0.1300E+03 0.7177E-02 250 0.91797 -0.24298 16 15 0.1199E-01 11 15 0.1240E+03 0.5280E-02 260 0.91865 -0.24494 16 15 0.1753E-01 11 15 0.1289E+03 0.7289E-02 270 0.91910 -0.24339 38 14 0.1210E-01 11 15 0.1230E+03 0.5327E-02 280 0.91969 -0.24532 16 15 0.1765E-01 11 15 0.1280E+03 0.7384E-02 290 0.92005 -0.24373 38 14 0.1223E-01 11 15 0.1223E+03 0.5367E-02 300 0.92057 -0.24565 28 15 0.1787E-01 11 15 0.1272E+03 0.7464E-02 310 0.92086 -0.24402 38 14 0.1235E-01 11 15 0.1216E+03 0.5401E-02 320 0.92131 -0.24592 28 15 0.1808E-01 11 15 0.1266E+03 0.7533E-02 330 0.92155 -0.24427 38 14 0.1244E-01 11 15 0.1210E+03 0.5429E-02 340 0.92195 -0.24616 28 15 0.1826E-01 11 15 0.1260E+03 0.7592E-02 350 0.92214 -0.24448 38 14 0.1253E-01 11 15 0.1205E+03 0.5452E-02 360 0.92250 -0.24636 28 15 0.1841E-01 11 15 0.1255E+03 0.7642E-02 370 0.92264 -0.24467 38 14 0.1259E-01 11 15 0.1201E+03 0.5473E-02 380 0.92297 -0.24653 28 15 0.1849E-01 11 15 0.1252E+03 0.7670E-02 390 0.92308 -0.24482 38 14 0.1264E-01 11 15 0.1199E+03 0.5489E-02 400 0.92337 -0.24667 28 15 0.1855E-01 11 15 0.1250E+03 0.7689E-02 410 0.92344 -0.24496 38 14 0.1269E-01 11 15 0.1198E+03 0.5502E-02 420 0.92370 -0.24679 28 15 0.1860E-01 11 15 0.1249E+03 0.7706E-02 430 0.92376 -0.24507 38 14 0.1272E-01 11 15 0.1197E+03 0.5512E-02 440 0.92399 -0.24689 28 15 0.1865E-01 11 15 0.1247E+03 0.7720E-02 450 0.92402 -0.24516 38 14 0.1275E-01 11 15 0.1195E+03 0.5521E-02 460 0.92424 -0.24697 28 15 0.1868E-01 11 15 0.1246E+03 0.7732E-02 470 0.92425 -0.24525 38 14 0.1278E-01 11 15 0.1194E+03 0.5529E-02 480 0.92445 -0.24705 28 15 0.1872E-01 11 15 0.1245E+03 0.7742E-02 490 0.92444 -0.24531 38 14 0.1280E-01 11 15 0.1194E+03 0.5535E-02 500 0.92462 -0.24711 28 15 0.1874E-01 11 15 0.1244E+03 0.7750E-02 510 0.92460 -0.24537 38 14 0.1282E-01 11 15 0.1193E+03 0.5541E-02 520 0.92477 -0.24716 28 15 0.1877E-01 11 15 0.1243E+03 0.7758E-02 530 0.92474 -0.24542 38 14 0.1284E-01 11 15 0.1192E+03 0.5546E-02 540 0.92490 -0.24721 28 15 0.1879E-01 11 15 0.1243E+03 0.7764E-02 550 0.92486 -0.24547 38 14 0.1285E-01 11 15 0.1192E+03 0.5551E-02 560 0.92501 -0.24725 28 15 0.1880E-01 11 15 0.1242E+03 0.7769E-02 570 0.92496 -0.24550 38 14 0.1286E-01 11 15 0.1192E+03 0.5553E-02 580 0.92511 -0.24728 28 15 0.1882E-01 11 15 0.1242E+03 0.7774E-02 590 0.92505 -0.24553 38 14 0.1287E-01 11 15 0.1191E+03 0.5557E-02 600 0.92519 -0.24731 28 15 0.1883E-01 11 15 0.1241E+03 0.7778E-02 610 0.92512 -0.24556 38 14 0.1288E-01 11 15 0.1191E+03 0.5559E-02 620 0.92525 -0.24733 28 15 0.1884E-01 11 15 0.1241E+03 0.7781E-02 630 0.92518 -0.24558 38 14 0.1289E-01 11 15 0.1191E+03 0.5561E-02 640 0.92531 -0.24735 28 15 0.1885E-01 11 15 0.1240E+03 0.7784E-02 650 0.92524 -0.24560 38 14 0.1289E-01 11 15 0.1190E+03 0.5563E-02 660 0.92536 -0.24737 28 15 0.1885E-01 11 15 0.1240E+03 0.7786E-02 670 0.92528 -0.24562 38 14 0.1290E-01 11 15 0.1190E+03 0.5565E-02 680 0.92540 -0.24739 28 15 0.1886E-01 11 15 0.1240E+03 0.7788E-02 690 0.92532 -0.24563 38 14 0.1290E-01 11 15 0.1190E+03 0.5566E-02 700 0.92544 -0.24740 28 15 0.1887E-01 11 15 0.1240E+03 0.7790E-02 710 0.92536 -0.24564 38 14 0.1291E-01 11 15 0.1190E+03 0.5567E-02 720 0.92547 -0.24741 28 15 0.1887E-01 11 15 0.1240E+03 0.7792E-02 730 0.92538 -0.24565 38 14 0.1291E-01 11 15 0.1190E+03 0.5568E-02 740 0.92550 -0.24742 28 15 0.1887E-01 11 15 0.1240E+03 0.7792E-02 750 0.92541 -0.24566 38 14 0.1291E-01 11 15 0.1190E+03 0.5569E-02 ****** ITERATION LIMIT REACHED ****** FORCE COEFFICIENTS, PRESSURE COEFFICIENT, AND MACH NUMBER (OR SIMILARITY PARAMETER) ON BODY AND DIVIDING STREAM LINE. MEDIUM MESH CL = 0.925408 CM = -0.245663 CP* = -0.603170 LOWER UPPER Y=0- Y=0+ I X CP M1 CP M1 1 -1.075000 0.053618 0.723608 0.053618 0.723608 B * 2 -0.825000 0.069312 0.715699 0.069312 0.715699 B * 3 -0.575000 0.091996 0.704111 0.091996 0.704111 B * 4 -0.350000 0.140921 0.678443 0.140921 0.678443 B * 5 -0.175000 0.233098 0.627237 0.233098 0.627237 B * 6 -0.075000 0.386578 0.531133 0.386578 0.531133 B * 7 -0.035000 0.525101 0.426176 0.525101 0.426176 B * 8 -0.015000 0.651223 0.300243 0.651223 0.300243 B * 9 -0.002500 0.725009 0.191378 0.725009 0.191378 B * AIRFOIL LEADING EDGE AIRFOIL LEADING EDGE 10 0.007500 0.754713 0.122803 1.024194 0.000000 U L * 11 0.017500 0.460883 0.477709 0.698990 0.235581 U L * 12 0.027500 0.318602 0.575680 0.448430 0.487071 U L * 13 0.037500 0.217392 0.636253 0.024145 0.738232 L U * 14 0.055000 0.122012 0.688477 -0.988792 1.131241 L * U 15 0.075000 0.055644 0.722592 -1.340896 1.238991 L * U 16 0.097500 0.003827 0.748147 -0.853903 1.087136 L * U 17 0.140625 -0.045364 0.771624 -0.611746 1.003106 L * 18 0.203125 -0.085805 0.790403 -0.784898 1.063867 L * U 19 0.265625 -0.118659 0.805337 -0.904981 1.104045 L * U 20 0.328125 -0.140230 0.814993 -1.026277 1.143195 L * U 21 0.390625 -0.145350 0.817268 -1.152993 1.182711 L * U 22 0.453125 -0.107492 0.800292 -1.261652 1.215574 L * U 23 0.515625 -0.029470 0.764118 -1.330207 1.235858 L * U 24 0.578125 0.052371 0.724233 -1.379016 1.250099 L * U 25 0.640625 0.134828 0.681693 -1.413424 1.260042 L * U 26 0.703125 0.217607 0.636131 -1.433220 1.265727 L * U 27 0.765625 0.306267 0.583399 -1.147150 1.180918 L * U 28 0.828125 0.388879 0.529559 -0.346937 0.902300 L U * 29 0.885000 0.463170 0.475969 0.173319 0.660898 L U * 30 0.915000 0.506282 0.441901 0.198642 0.646853 L U * 31 0.945000 0.538848 0.414312 0.221937 0.633657 L U * 32 0.975000 0.479313 0.463506 0.287337 0.595050 L U * 33 1.000000 0.432380 0.498879 0.359740 0.549152 L U * AIRFOIL TRAILING EDGE AIRFOIL TRAILING EDGE 34 1.025000 0.330808 0.567938 0.330808 0.567938 B * 35 1.090000 0.242293 0.621897 0.242293 0.621897 B * 36 1.225000 0.164132 0.665920 0.164132 0.665920 B * 37 1.400000 0.115726 0.691780 0.115726 0.691780 B * 38 1.625000 0.087815 0.706261 0.087815 0.706261 B * 39 1.875000 0.054550 0.723141 0.054550 0.723141 B * Y(J) J= 1 TO 28 -5.20000 -3.60000 -2.40000 -1.60000 -1.15000 -0.800000 -0.550000 -0.390000 -0.300000 -0.240000 -0.180000 -0.125000 -0.750000E-01-0.300000E-01 0.300000E-01 0.750000E-01 0.125000 0.180000 0.240000 0.300000 0.390000 0.550000 0.800000 1.15000 1.60000 2.40000 3.60000 5.20000 WE = 1.9500 EPS = 0.2000 MAXIT FOR THIS MESH = 1500 ITERATION CL CM IERR JERR ERROR IRL JRL BIGRL ERCIRC 10 0.93194 -0.25329 33 29 0.1976E-02 17 28 0.2384E+03 0.1203E-02 20 0.94078 -0.25689 43 28 0.9133E-03 17 20 0.8492E+02 0.1507E-02 30 0.94954 -0.26019 45 28 0.9049E-03 17 28 0.5427E+02 0.1438E-02 40 0.95801 -0.26323 45 28 0.9526E-03 17 28 0.5104E+02 0.1352E-02 50 0.96544 -0.26549 45 28 0.8877E-03 17 28 0.6178E+02 0.1166E-02 60 0.97168 -0.26735 44 28 0.7757E-03 17 28 0.7641E+02 0.9310E-03 70 0.97632 -0.26868 44 28 0.6507E-03 17 28 0.8944E+02 0.7091E-03 80 0.98008 -0.26976 44 28 0.5593E-03 17 28 0.9751E+02 0.5705E-03 90 0.98298 -0.27058 44 28 0.4713E-03 17 28 0.9891E+02 0.4373E-03 100 0.98529 -0.27129 44 28 0.3945E-03 17 28 0.9575E+02 0.3570E-03 110 0.98720 -0.27192 44 28 0.3439E-03 17 28 0.8942E+02 0.2953E-03 120 0.98880 -0.27249 44 28 0.2944E-03 17 28 0.8136E+02 0.2495E-03 130 0.99017 -0.27302 44 28 0.2563E-03 17 28 0.7301E+02 0.2153E-03 140 0.99137 -0.27350 44 28 0.2257E-03 17 28 0.6492E+02 0.1901E-03 150 0.99243 -0.27395 44 28 0.1988E-03 17 28 0.5754E+02 0.1690E-03 160 0.99337 -0.27437 44 28 0.1765E-03 17 28 0.5098E+02 0.1497E-03 170 0.99421 -0.27474 44 28 0.1565E-03 17 28 0.4527E+02 0.1324E-03 180 0.99495 -0.27507 44 28 0.1391E-03 17 28 0.4021E+02 0.1185E-03 190 0.99562 -0.27537 44 28 0.1244E-03 17 28 0.3579E+02 0.1069E-03 200 0.99623 -0.27565 44 28 0.1116E-03 17 28 0.3189E+02 0.9727E-04 210 0.99678 -0.27590 44 28 0.1007E-03 17 28 0.2841E+02 0.8941E-04 220 0.99729 -0.27613 44 28 0.9098E-04 17 28 0.2535E+02 0.8142E-04 230 0.99775 -0.27634 44 28 0.8250E-04 17 28 0.2267E+02 0.7486E-04 240 0.99818 -0.27653 44 28 0.7507E-04 17 28 0.2031E+02 0.6831E-04 250 0.99857 -0.27670 44 28 0.6821E-04 17 28 0.1815E+02 0.6270E-04 260 0.99893 -0.27686 44 28 0.6202E-04 17 28 0.1635E+02 0.5758E-04 270 0.99926 -0.27700 44 28 0.5658E-04 17 28 0.1481E+02 0.5352E-04 280 0.99956 -0.27713 44 28 0.5120E-04 17 28 0.1334E+02 0.4768E-04 290 0.99983 -0.27725 44 28 0.4618E-04 17 28 0.1201E+02 0.4268E-04 300 1.00007 -0.27735 44 28 0.4181E-04 17 28 0.1085E+02 0.3815E-04 310 1.00029 -0.27744 44 27 0.3732E-04 17 28 0.9868E+01 0.3469E-04 320 1.00048 -0.27752 44 28 0.3421E-04 17 28 0.8956E+01 0.3159E-04 330 1.00066 -0.27760 44 28 0.3071E-04 17 28 0.8011E+01 0.2873E-04 340 1.00082 -0.27767 44 28 0.2767E-04 17 28 0.7313E+01 0.2623E-04 350 1.00097 -0.27773 44 28 0.2532E-04 17 28 0.6567E+01 0.2384E-04 360 1.00110 -0.27778 44 28 0.2293E-04 17 28 0.5897E+01 0.2110E-04 370 1.00123 -0.27784 44 28 0.2083E-04 17 28 0.5375E+01 0.1967E-04 380 1.00134 -0.27788 44 28 0.1894E-04 17 28 0.4851E+01 0.1812E-04 390 1.00144 -0.27793 44 28 0.1726E-04 17 28 0.4357E+01 0.1645E-04 400 1.00153 -0.27796 44 28 0.1589E-04 17 28 0.3902E+01 0.1490E-04 410 1.00162 -0.27800 44 28 0.1434E-04 17 28 0.3582E+01 0.1359E-04 420 1.00169 -0.27803 44 28 0.1314E-04 17 28 0.3228E+01 0.1252E-04 430 1.00176 -0.27806 44 28 0.1179E-04 17 28 0.2980E+01 0.1121E-04 440 1.00183 -0.27809 44 27 0.1048E-04 17 28 0.2633E+01 0.1001E-04 450 1.00188 -0.27811 44 28 0.9641E-05 17 28 0.2417E+01 0.9060E-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 = 0.0000000 K = 2.3977063 DOUBLET STRENGTH = 0.6309681 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 = 1.001883 CM = -0.278109 CP* = -0.603170 LOWER UPPER Y=0- Y=0+ I X CP M1 CP M1 1 -1.075000 0.068365 0.716179 0.068365 0.716179 B * 2 -0.950000 0.072985 0.713836 0.072985 0.713836 B * 3 -0.825000 0.079064 0.710741 0.079064 0.710741 B * 4 -0.700000 0.088629 0.705843 0.088629 0.705843 B * 5 -0.575000 0.103370 0.698228 0.103370 0.698228 B * 6 -0.450000 0.125312 0.686736 0.125312 0.686736 B * 7 -0.350000 0.156545 0.670039 0.156545 0.670039 B * 8 -0.250000 0.202634 0.644610 0.202634 0.644610 B * 9 -0.175000 0.265232 0.608373 0.265232 0.608373 B * 10 -0.125000 0.345674 0.558364 0.345674 0.558364 B * 11 -0.075000 0.455684 0.481640 0.455684 0.481640 B * 12 -0.052500 0.575045 0.381313 0.575045 0.381313 B * 13 -0.035000 0.692789 0.244941 0.692789 0.244941 B * 14 -0.022500 0.814602 0.000000 0.814602 0.000000 B * 15 -0.015000 0.928782 0.000000 0.928782 0.000000 B * 16 -0.007500 1.042220 0.000000 1.042220 0.000000 B * 17 -0.002500 1.154985 0.000000 1.154985 0.000000 B * AIRFOIL LEADING EDGE AIRFOIL LEADING EDGE 18 0.002500 1.184278 0.000000 1.303658 0.000000 U L * 19 0.007500 0.616428 0.339681 1.104766 0.000000 U L * 20 0.012500 0.363161 0.546888 0.907023 0.000000 U L * 21 0.017500 0.220336 0.634573 0.708279 0.220819 U L * 22 0.022500 0.150426 0.673343 0.507206 0.441141 U L * 23 0.027500 0.122936 0.687990 0.303374 0.585194 U L * 24 0.032500 0.104277 0.697757 0.097425 0.701309 B * 25 0.037500 0.081650 0.709420 -0.140487 0.815108 L U * 26 0.045000 0.053509 0.723663 -0.587138 0.994169 L * 27 0.055000 0.027600 0.736533 -1.003696 1.136009 L * U 28 0.065000 0.012221 0.744067 -1.176866 1.190009 L * U 29 0.075000 0.003845 0.748138 -1.276120 1.219883 L * U 30 0.085000 -0.005555 0.752681 -1.271454 1.218495 L * U 31 0.097500 -0.019543 0.759391 -1.125406 1.174221 L * U 32 0.115000 -0.036096 0.767256 -0.909017 1.105369 L * U 33 0.140625 -0.052093 0.774781 -0.791712 1.066188 L * U 34 0.171875 -0.068680 0.782506 -0.758631 1.054875 L * U 35 0.203125 -0.085558 0.790290 -0.749833 1.051846 L * U 36 0.234375 -0.099936 0.796861 -0.804592 1.070560 L * U 37 0.265625 -0.113574 0.803044 -0.884116 1.097169 L * U 38 0.296875 -0.125108 0.808236 -0.951179 1.119117 L * U 39 0.328125 -0.131433 0.811069 -1.004883 1.136387 L * U 40 0.359375 -0.141243 0.815444 -1.063726 1.155014 L * U 41 0.390625 -0.150929 0.819740 -1.140083 1.178746 L * U 42 0.421875 -0.134951 0.812641 -1.209374 1.199875 L * U 43 0.453125 -0.097429 0.795719 -1.257631 1.214374 L * U 44 0.484375 -0.059009 0.778011 -1.296630 1.225965 L * U 45 0.515625 -0.020552 0.759873 -1.330860 1.236050 L * U 46 0.546875 0.019683 0.740421 -1.359725 1.244490 L * U 47 0.578125 0.060441 0.720181 -1.384943 1.251818 L * U 48 0.609375 0.101374 0.699264 -1.407007 1.258194 L * U 49 0.640625 0.142746 0.677467 -1.425004 1.263370 L * U 50 0.671875 0.184818 0.654557 -1.439743 1.267595 L * U 51 0.703125 0.227900 0.630235 -1.451983 1.271092 L * U 52 0.734375 0.271895 0.604388 -1.461137 1.273701 L * U 53 0.765625 0.316321 0.577115 -1.466383 1.275194 L * U 54 0.796875 0.361065 0.548276 -1.466894 1.275339 L * U 55 0.828125 0.405170 0.518282 -0.961867 1.122576 L * U 56 0.859375 0.443193 0.490955 -0.120576 0.806200 L U * 57 0.885000 0.474284 0.467424 0.219101 0.635278 L U * 58 0.900000 0.505215 0.442776 0.223842 0.632566 L U * 59 0.915000 0.540114 0.413203 0.229329 0.629412 L U * 60 0.930000 0.571718 0.384465 0.237650 0.624599 L U * 61 0.945000 0.582873 0.373795 0.251674 0.616402 L U * 62 0.960000 0.558696 0.396558 0.274949 0.602553 L U * 63 0.975000 0.507894 0.440575 0.311184 0.580334 L U * 64 0.990000 0.464965 0.474599 0.362300 0.547459 L U * 65 1.000000 0.454125 0.482812 0.427164 0.502656 LU * AIRFOIL TRAILING EDGE AIRFOIL TRAILING EDGE 66 1.010000 0.404831 0.518519 0.404831 0.518519 B * 67 1.025000 0.355488 0.551953 0.355488 0.551953 B * 68 1.050000 0.305500 0.583875 0.305500 0.583875 B * 69 1.090000 0.256270 0.613693 0.256270 0.613693 B * 70 1.150000 0.211189 0.639779 0.211189 0.639779 B * 71 1.225000 0.174966 0.659993 0.174966 0.659993 B * 72 1.300000 0.146920 0.675229 0.146920 0.675229 B * 73 1.400000 0.124461 0.687185 0.124461 0.687185 B * 74 1.500000 0.107076 0.696300 0.107076 0.696300 B * 75 1.625000 0.094012 0.703072 0.094012 0.703072 B * 76 1.750000 0.085248 0.707578 0.085248 0.707578 B * 77 1.875000 0.078596 0.710979 0.078596 0.710979 B * Y(J) J= 1 TO 56 -5.20000 -4.40000 -3.60000 -3.00000 -2.40000 -1.95000 -1.60000 -1.35000 -1.15000 -0.950000 -0.800000 -0.650000 -0.550000 -0.450000 -0.390000 -0.340000 -0.300000 -0.270000 -0.240000 -0.210000 -0.180000 -0.150000 -0.125000 -0.100000 -0.750000E-01-0.500000E-01-0.300000E-01-0.100000E-01 0.100000E-01 0.300000E-01 0.500000E-01 0.750000E-01 0.100000 0.125000 0.150000 0.180000 0.210000 0.240000 0.270000 0.300000 0.340000 0.390000 0.450000 0.550000 0.650000 0.800000 0.950000 1.15000 1.35000 1.60000 1.95000 2.40000 3.00000 3.60000 4.40000 5.20000 FLOW AT EACH GRID POINT. P PARABOLIC H HYPERBOLIC S SHOCK - ELLIPTIC 56 --------------------------------------------------------------------------- 55 --------------------------------------------------------------------------- 54 --------------------------------------------------------------------------- 53 --------------------------------------------------------------------------- 52 --------------------------------------------------------------------------- 51 --------------------------------------------------------------------------- 50 --------------------------------------------------------------------------- 49 --------------------------------------------------------------------------- 48 --------------------------------------------------------------------------- 47 --------------------------------------------------------------------------- 46 ---------------------------------------------PHHHHHS----------------------- 45 ------------------------------------------PHHHHHHHHHS---------------------- 44 ----------------------------------------PHHHHHHHHHHHHS--------------------- 43 --------------------------------------PHHHHHHHHHHHHHHS--------------------- 42 --------------------------------------PHHHHHHHHHHHHHHHS-------------------- 41 -------------------------------------PHHHHHHHHHHHHHHHHS-------------------- 40 ------------------------------------PHHHHHHHHHHHHHHHHHS-------------------- 39 ------------------------------------PHHHHHHHHHHHHHHHHHS-------------------- 38 -----------------------------------PHHHHHHHHHHHHHHHHHHS-------------------- 37 -----------------------------------PHHHHHHHHHHHHHHHHHHS-------------------- 36 ----------------------------------PHHHHHHHHHHHHHHHHHHHS-------------------- 35 ----------------------------------PHHHHHHHHHHHHHHHHHHHS-------------------- 34 -------------------------------PSPHHHHHHHHHHHHHHHHHHHHS-------------------- 33 -----------------------------PHHHHHHHHHHHHHHHHHHHHHHHHS-------------------- 32 ----------------------------PHHHHHHHHHHHHHHHHHHHHHHHHHS-------------------- 31 ---------------------------PHHHHHHHHHHHHHHHHHHHHHHHHHHS-------------------- 30 --------------------------PHHHHHHHHHHHHHHHHHHHHHHHHHHHS-------------------- 29 -------------------------PHHHHHHHHHHHHHHHHHHHHHHHHHHHHS-------------------- 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 8888888888888888888888888888888888888888888888888888888888888888888888888888 8888888888888888888888888888888888888888888888888888888888888888888888888888 8888888888888888888888888888888888888888888888888888888888888888888888888888 8888888888888888888888888888888888888888888888888888888888888888888888888888 8888888888888888888888888888888888888888888888888888888888888888888888888888 8888888888888888888888888888888888888888888888888888888888888888888888888888 8888888888888888888888888888888888888899999999999998888888888888888888888888 8888888888888888888888888888888888999999999999999999999888888888888888888888 7888888888888888888888888888888899999999999999999999999998888888888888888888 7788888888888888888888888888888999999999999********9999998888888888888888877 7777888888888888888888888888889999999999************999988888888888888888777 77777888888888888888888888888899999999********111111*99888888888888888877777 7777778888888888888888888888889999999*******11111111198888888888888887777777 777777778888888888888888888889999999******11111111221*8888888888887777777777 77777777788888888888888888888999999******111111122222*8888877777777777777777 7777777777888888888888888888999999******1111112222222*8777777777777777777777 7777777777788888888888888888999999*****1111112222222218777777777777777777777 777777777777888888888888888899999*****11111112222222218777777777777777777777 77777777777777888888888888889999******11111122222222218777777777777777777777 77777777777777778888888888899999*****111111222222222218777777777777777777777 7777777777777777777888888889999******111112222222222218777777777777777777777 777777777777777777777888888999******1111112222222223318777777777777777777777 77777777666677777777778888999*******1111122222222233318777777666666777777777 7777777666666666777777788899*******11111222222222333318776666666666677777777 777777766666666666677778889**11****11111222222223333318666666666666677777777 77777776655555555566677789**1111***11112222222233333318666666666666667777777 7777776665443333344566778**11111**111112222222333333318666666666666667777777 +77777766654300000013567891122211**111122222222333333318666666665566667777777 -7777776665420000045667777777788888888888888877777666655554444555556667777777 7777776665443333445566667777777888888888888877777666655555555555556667777777 7777776665544445555566666777777788888888888777777666655555555555566667777777 7777776665555555556666666677777788888888888777777666665555555555666667777777 7777776666555666666666666677777778888888887777777666666555555566666667777777 7777776666666666666666666677777777888888887777777666666666666666666667777777 7777776666666666666666666677777777788888877777777666666666666666666667777777 7777776666666666666666666777777777777888777777777666666666666666666667777777 7777776666666666666666677777777777777777777777777666666666666666666667777777 7777777666666666666667777777777777777777777777777766666666666666666667777777 7777777666666666777777777777777777777777777777777766666666666666666667777777 7777777666667777777777777777777777777777777777777776666666666666666667777777 7777777777777777777777777777777777777777777777777776666666666666666667777777 7777777777777777777777777777777777777777777777777777666666666666666677777777 7777777777777777777777777777777777777777777777777777777666666666667777777777 7777777777777777777777777777777777777777777777777777777777777777777777777777 7777777777777777777777777777777777777777777777777777777777777777777777777777 7777777777777777777777777777777777777777777777777777777777777777777777777777 7777777777777777777777777777777777777777777777777777777777777777777777777777 7777777777777777777777777777777777777777777777777777777777777777777777777777 7777777777777777777777777777777777777777777777777777777777777777777777777777 7777777777777777777777777777777777777777777777777777777777777777777777777777 7777777777777777777777777777777777777777777777777777777777777777777777777777 7777777777777777777777777777777777777777777777777777777777777777777777777777 7777777777777777777777777777777777777777777777777777777777777777777777777777 7777777777777777777777777777777777777777777777777777777777777777777777777777 7777777777777777777777777777777777777777777777777777777777777777777777777777 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 U UUUU U U UU U UU UU U U U U U U U U U U U U UUU - - - - - - - - - - -----U------ --- ---- ---- --- ---- ----------- - - - - - - - - - U LL L LLL L L L U LLL L LLL LL B B B L L B B B B LB L B B B B B L L L B B B L L UUU B B U L U B B B L L U B L L UB B L LB U LL L B LLL L B U B U B B U B U SONIC LINE COORDINATES Y XSONIC 0.80000 0.55476 0.74523 0.65000 0.46045 0.79233 0.55000 0.40885 0.81164 0.45000 0.35817 0.82421 0.39000 0.32991 0.82974 0.34000 0.30616 0.83358 0.30000 0.28692 0.83591 0.27000 0.27255 0.83729 0.24000 0.25797 0.83840 0.21000 0.24341 0.83926 0.18000 0.22813 0.83991 0.15000 0.21189 0.84039 0.12500 0.11696 0.15519 0.19163 0.84069 0.10000 0.09628 0.84092 0.07500 0.08350 0.84109 0.05000 0.07124 0.84122 0.03000 0.06049 0.84132 0.01000 0.04896 0.84140 BODY LOCATION SONIC LINE PLOT Y VS X * FOR SONIC POINTS + + + + + + + + + + + ....................................................................................................... 1.5 + . . + . . . . . . . . . . . . . . . . . . 1.0 + . . + . . . . . . . * * . . . . . . * * . . . . * * . 0.5 + . . + . * * . . * * . . * * . . * * . . ** ** . . ** * . . * * . . *** * * . . ** * . 0.0 + . -*-------------BODY SLIT---------*----- . + . . . . . . . . . . . . . . . . . . -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 ( 38 PTS) INVISCID WAKE PROFILES FOR INDIVIDUAL SHOCK WAVES WITHIN MOMENTUM CONTOUR SHOCK 1 WAVE DRAG FOR THIS SHOCK= 0.041388 Y CD(Y) PO/POINF 0.00000000 0.13479130 0.91219378 0.01000000 0.13346204 0.91305971 0.03000000 0.13082983 0.91477436 0.05000000 0.12751186 0.91693580 0.07500001 0.12258558 0.92014486 0.10000000 0.11703099 0.92376328 0.12500000 0.11104543 0.92766243 0.15000002 0.10477512 0.93174702 0.18000001 0.09701583 0.93680161 0.20999999 0.08911416 0.94194895 0.24000001 0.08114161 0.94714242 0.27000001 0.07313413 0.95235872 0.30000004 0.06509925 0.95759284 0.34000000 0.05435449 0.96459222 0.39000002 0.04090958 0.97335052 0.44999999 0.02883136 0.98121858 0.55000001 0.01483259 0.99033773 0.64999998 0.00448016 0.99708152 0.80000001 0.00056499 0.99963194 CALCULATION OF DRAG COEFFICIENT BY MOMENTUM INTEGRAL METHOD BOUNDARIES OF CONTOUR USED CONTRIBUTION TO CD UPSTREAM X = -0.175000 CDUP = -0.001936 DOWNSTREAM X = 1.225000 CDDOWN = 0.001473 TOP Y = 4.400000 CDTOP = -0.000029 BOTTOM Y = -4.400000 CDBOT = 0.000009 TOTAL CONTRIBUTIONS AROUND CONTOUR = -0.000484 THERE ARE 1 SHOCKS INSIDE CONTOUR. TOTAL CDWAVE = 0.041388 NOTE - ALL SHOCKS CONTAINED WITHIN CONTOUR CDWAVE EQUALS TOTAL WAVE DRAG DRAG CALCULATED FROM MOMENTUM INTEGRAL CD = 0.040905 enter name of input data file *** Run time error - File ' ' not found