XFOIL Version 6.96 Calculated polar for: NASA/LANGLEY MS(1)-0317 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.000 -0.7144 0.09347 0.08709 -0.0554 1.0000 0.0443 -14.750 -0.7696 0.08033 0.07361 -0.0638 1.0000 0.0439 -14.500 -0.8047 0.07228 0.06526 -0.0681 1.0000 0.0439 -14.250 -0.8309 0.06621 0.05890 -0.0705 1.0000 0.0442 -14.000 -0.8520 0.06118 0.05357 -0.0718 1.0000 0.0445 -13.750 -0.8694 0.05688 0.04894 -0.0723 1.0000 0.0450 -13.500 -0.8654 0.05476 0.04680 -0.0721 1.0000 0.0455 -13.250 -0.8627 0.05261 0.04459 -0.0718 1.0000 0.0461 -13.000 -0.8610 0.05044 0.04232 -0.0713 1.0000 0.0468 -12.750 -0.8593 0.04829 0.04004 -0.0706 1.0000 0.0475 -12.500 -0.8571 0.04622 0.03781 -0.0696 1.0000 0.0483 -12.250 -0.8553 0.04426 0.03566 -0.0683 1.0000 0.0493 -12.000 -0.8547 0.04239 0.03353 -0.0665 1.0000 0.0505 -11.750 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0.8262 0.6905 -2.250 0.0401 0.02233 0.01455 -0.0601 0.8226 0.7027 -2.000 0.0642 0.02275 0.01497 -0.0581 0.8188 0.7089 -1.750 0.0868 0.02299 0.01519 -0.0574 0.8119 0.7183 -1.500 0.1134 0.02305 0.01521 -0.0571 0.8071 0.7241 -1.250 0.1412 0.02306 0.01519 -0.0567 0.8032 0.7277 -1.000 0.1708 0.02299 0.01507 -0.0569 0.7998 0.7320 -0.750 0.1949 0.02308 0.01515 -0.0571 0.7927 0.7376 -0.500 0.2247 0.02298 0.01502 -0.0579 0.7877 0.7422 -0.250 0.2527 0.02294 0.01497 -0.0576 0.7838 0.7449 0.000 0.2807 0.02290 0.01491 -0.0575 0.7792 0.7481 0.250 0.3040 0.02298 0.01502 -0.0570 0.7708 0.7519 0.500 0.3358 0.02278 0.01478 -0.0578 0.7651 0.7561 0.750 0.3689 0.02251 0.01447 -0.0591 0.7576 0.7607 1.000 0.3948 0.02222 0.01418 -0.0581 0.7460 0.7628 1.250 0.4203 0.02190 0.01385 -0.0569 0.7324 0.7655 1.500 0.4502 0.02146 0.01335 -0.0565 0.7203 0.7686 1.750 0.4769 0.02125 0.01316 -0.0562 0.7071 0.7720 2.000 0.5051 0.02109 0.01299 -0.0564 0.6945 0.7755 2.250 0.5379 0.02080 0.01267 -0.0573 0.6822 0.7795 2.500 0.5623 0.02066 0.01255 -0.0564 0.6676 0.7819 2.750 0.5865 0.02056 0.01249 -0.0555 0.6512 0.7844 3.000 0.6118 0.02044 0.01238 -0.0548 0.6329 0.7873 3.250 0.6380 0.02032 0.01224 -0.0543 0.6118 0.7907 3.500 0.6645 0.02026 0.01214 -0.0541 0.5851 0.7942 3.750 0.6922 0.02022 0.01200 -0.0542 0.5489 0.7975 4.000 0.7156 0.02028 0.01183 -0.0531 0.4985 0.7999 4.250 0.7333 0.02063 0.01181 -0.0511 0.4362 0.8024 4.500 0.7479 0.02127 0.01209 -0.0490 0.3786 0.8055 4.750 0.7629 0.02200 0.01251 -0.0472 0.3319 0.8089 5.000 0.7801 0.02272 0.01299 -0.0460 0.2948 0.8122 5.250 0.7995 0.02340 0.01349 -0.0453 0.2655 0.8154 5.500 0.8167 0.02405 0.01401 -0.0441 0.2437 0.8181 5.750 0.8327 0.02463 0.01451 -0.0424 0.2267 0.8209 6.000 0.8498 0.02521 0.01503 -0.0410 0.2130 0.8242 6.250 0.8672 0.02582 0.01559 -0.0398 0.2024 0.8277 6.500 0.8853 0.02645 0.01617 -0.0388 0.1932 0.8312 6.750 0.9054 0.02710 0.01679 -0.0383 0.1854 0.8345 7.000 0.9213 0.02769 0.01738 -0.0367 0.1786 0.8373 7.250 0.9376 0.02841 0.01805 -0.0354 0.1730 0.8407 7.500 0.9578 0.02903 0.01873 -0.0347 0.1672 0.8444 7.750 0.9779 0.02976 0.01945 -0.0341 0.1623 0.8482 8.000 0.9986 0.03062 0.02022 -0.0339 0.1584 0.8517 8.250 1.0185 0.03125 0.02094 -0.0330 0.1547 0.8546 8.500 1.0382 0.03194 0.02168 -0.0323 0.1511 0.8580 8.750 1.0580 0.03269 0.02246 -0.0316 0.1477 0.8620 9.000 1.0787 0.03353 0.02325 -0.0313 0.1448 0.8663 9.250 1.0997 0.03433 0.02409 -0.0308 0.1420 0.8703 9.500 1.1191 0.03507 0.02496 -0.0300 0.1393 0.8743 9.750 1.1397 0.03589 0.02585 -0.0295 0.1368 0.8785 10.000 1.1610 0.03676 0.02676 -0.0293 0.1344 0.8829 10.250 1.1806 0.03761 0.02764 -0.0287 0.1323 0.8871 10.500 1.2013 0.03848 0.02847 -0.0281 0.1303 0.8917 10.750 1.2198 0.03947 0.02961 -0.0275 0.1283 0.8973 11.000 1.2366 0.04048 0.03078 -0.0266 0.1263 0.9031 11.250 1.2528 0.04149 0.03195 -0.0257 0.1244 0.9097 11.500 1.2691 0.04255 0.03312 -0.0249 0.1226 0.9166 11.750 1.2838 0.04355 0.03420 -0.0238 0.1208 0.9243 12.000 1.3000 0.04454 0.03524 -0.0230 0.1192 0.9330 12.500 1.3278 0.04686 0.03775 -0.0210 0.1162 0.9647 12.750 1.3360 0.04853 0.03968 -0.0203 0.1146 1.0000 13.000 1.3460 0.05043 0.04180 -0.0200 0.1128 1.0000 13.250 1.3554 0.05233 0.04386 -0.0197 0.1111 1.0000 13.500 1.3655 0.05417 0.04582 -0.0195 0.1095 1.0000 13.750 1.3772 0.05590 0.04761 -0.0194 0.1081 1.0000 14.000 1.3927 0.05740 0.04911 -0.0195 0.1066 1.0000 14.250 1.4023 0.05943 0.05121 -0.0193 0.1052 1.0000 14.500 1.3925 0.06279 0.05492 -0.0186 0.1040 1.0000 14.750 1.3819 0.06642 0.05884 -0.0182 0.1027 1.0000 15.000 1.3708 0.07024 0.06292 -0.0181 0.1014 1.0000 15.250 1.3596 0.07420 0.06711 -0.0183 0.1001 1.0000 15.500 1.3494 0.07820 0.07130 -0.0189 0.0989 1.0000 15.750 1.3413 0.08208 0.07532 -0.0196 0.0978 1.0000 16.000 1.3378 0.08555 0.07889 -0.0205 0.0967 1.0000 16.250 1.3462 0.08767 0.08102 -0.0209 0.0956 1.0000 16.500 1.3266 0.09352 0.08706 -0.0229 0.0947 1.0000 16.750 1.2404 0.11040 0.10452 -0.0317 0.0942 1.0000