XFOIL Version 6.96 Calculated polar for: NASA/LANGLEY NLF(2)-0415 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 ------ -------- --------- --------- -------- -------- -------- -12.000 -0.3708 0.10393 0.09860 -0.1007 0.9529 0.0305 -11.750 -0.3734 0.09840 0.09307 -0.1038 0.9511 0.0301 -11.500 -0.3790 0.09260 0.08725 -0.1074 0.9495 0.0297 -11.250 -0.3868 0.08696 0.08156 -0.1110 0.9480 0.0290 -11.000 -0.4010 0.08125 0.07577 -0.1146 0.9463 0.0287 -10.750 -0.4254 0.07817 0.07265 -0.1129 0.9416 0.0285 -10.500 -0.4447 0.07447 0.06887 -0.1130 0.9384 0.0281 -10.250 -0.4631 0.07090 0.06516 -0.1132 0.9357 0.0282 -10.000 -0.4777 0.06742 0.06152 -0.1135 0.9334 0.0281 -9.750 -0.5065 0.06652 0.06057 -0.1078 0.9283 0.0279 -9.500 -0.5328 0.06531 0.05928 -0.1025 0.9244 0.0278 -9.250 -0.5494 0.06308 0.05688 -0.0990 0.9216 0.0273 -9.000 -0.5581 0.06064 0.05423 -0.0965 0.9196 0.0277 -8.750 -0.5674 0.05849 0.05187 -0.0930 0.9172 0.0277 -8.500 -0.5859 0.05738 0.05063 -0.0868 0.9135 0.0278 -8.250 -0.5941 0.05539 0.04841 -0.0826 0.9113 0.0280 -8.000 -0.5957 0.05312 0.04587 -0.0794 0.9095 0.0278 -7.750 -0.5924 0.05060 0.04304 -0.0768 0.9080 0.0274 -7.500 -0.5827 0.04802 0.04011 -0.0751 0.9066 0.0270 -7.250 -0.5685 0.04545 0.03717 -0.0738 0.9054 0.0268 -7.000 -0.5522 0.04322 0.03456 -0.0725 0.9045 0.0267 -6.750 -0.5335 0.04127 0.03228 -0.0715 0.9039 0.0267 -6.500 -0.5195 0.03978 0.03054 -0.0694 0.9029 0.0268 -6.250 -0.5086 0.03857 0.02914 -0.0666 0.9017 0.0270 -6.000 -0.4954 0.03755 0.02795 -0.0643 0.9001 0.0278 -5.750 -0.4793 0.03670 0.02690 -0.0624 0.8986 0.0294 -5.500 -0.4609 0.03576 0.02579 -0.0608 0.8976 0.0301 -5.250 -0.4422 0.03487 0.02479 -0.0591 0.8967 0.0305 -5.000 -0.4237 0.03407 0.02390 -0.0575 0.8958 0.0309 -4.750 -0.4049 0.03331 0.02312 -0.0560 0.8946 0.0313 -4.500 -0.3869 0.03241 0.02226 -0.0546 0.8933 0.0322 -4.250 -0.3688 0.03175 0.02159 -0.0534 0.8922 0.0331 -4.000 -0.3498 0.03124 0.02105 -0.0524 0.8913 0.0344 -3.750 -0.3285 0.03084 0.02058 -0.0519 0.8904 0.0370 -3.500 -0.3038 0.03051 0.02012 -0.0519 0.8894 0.0406 -3.250 -0.2859 0.03003 0.01954 -0.0509 0.8877 0.0442 -3.000 -0.2711 0.02974 0.01917 -0.0493 0.8860 0.0483 -2.750 -0.2525 0.02934 0.01874 -0.0484 0.8842 0.0598 -2.500 -0.2362 0.02734 0.01898 -0.0489 0.8825 0.5701 -2.250 -0.2209 0.02898 0.02067 -0.0449 0.8804 0.6266 -2.000 -0.2067 0.03037 0.02211 -0.0404 0.8786 0.6561 -1.750 -0.1881 0.03127 0.02300 -0.0374 0.8768 0.6743 -1.500 -0.1637 0.03168 0.02331 -0.0365 0.8754 0.6845 -1.250 -0.1345 0.03169 0.02314 -0.0377 0.8745 0.6852 -1.000 -0.1158 0.03167 0.02301 -0.0369 0.8720 0.6860 -0.750 -0.0966 0.03166 0.02290 -0.0362 0.8691 0.6869 -0.500 -0.0734 0.03171 0.02287 -0.0362 0.8670 0.6882 -0.250 -0.0472 0.03177 0.02282 -0.0368 0.8649 0.6893 0.000 -0.0190 0.03184 0.02281 -0.0377 0.8630 0.6901 0.250 0.0102 0.03196 0.02285 -0.0388 0.8615 0.6910 0.500 0.0412 0.03210 0.02292 -0.0402 0.8601 0.6919 0.750 0.0612 0.03222 0.02300 -0.0397 0.8568 0.6929 1.000 0.0812 0.03235 0.02309 -0.0393 0.8533 0.6940 1.250 0.1073 0.03251 0.02322 -0.0398 0.8505 0.6953 1.500 0.1351 0.03270 0.02341 -0.0405 0.8482 0.6964 1.750 0.1651 0.03291 0.02363 -0.0415 0.8463 0.6973 2.000 0.1971 0.03315 0.02390 -0.0429 0.8447 0.6982 2.250 0.2071 0.03334 0.02413 -0.0405 0.8385 0.6993 2.500 0.2330 0.03356 0.02439 -0.0409 0.8351 0.7003 2.750 0.2628 0.03378 0.02466 -0.0419 0.8326 0.7013 3.000 0.2955 0.03402 0.02498 -0.0434 0.8306 0.7025 3.250 0.3092 0.03427 0.02529 -0.0417 0.8240 0.7037 3.500 0.3362 0.03450 0.02560 -0.0422 0.8200 0.7050 3.750 0.3681 0.03471 0.02590 -0.0436 0.8173 0.7064 4.250 0.4154 0.03513 0.02652 -0.0434 0.8059 0.7098 4.500 0.4524 0.03463 0.02615 -0.0448 0.7966 0.7113 4.750 0.4961 0.03301 0.02471 -0.0460 0.7788 0.7127 5.000 0.5394 0.03116 0.02302 -0.0471 0.7609 0.7142 5.250 0.5606 0.03027 0.02227 -0.0454 0.7419 0.7158 5.500 0.5761 0.02991 0.02206 -0.0432 0.7225 0.7175 5.750 0.5900 0.02970 0.02203 -0.0409 0.6993 0.7193 6.000 0.6033 0.02960 0.02208 -0.0385 0.6684 0.7212 6.250 0.6956 0.02429 0.01525 -0.0425 0.3632 0.7232 6.500 0.7054 0.02562 0.01578 -0.0402 0.2325 0.7251 6.750 0.7245 0.02642 0.01626 -0.0393 0.1746 0.7268 7.000 0.7440 0.02715 0.01683 -0.0385 0.1429 0.7286 7.250 0.7638 0.02785 0.01750 -0.0376 0.1238 0.7307 7.500 0.7832 0.02860 0.01825 -0.0368 0.1092 0.7332 7.750 0.8022 0.02941 0.01903 -0.0360 0.0980 0.7360 8.000 0.8226 0.03018 0.01989 -0.0353 0.0894 0.7389 8.250 0.8423 0.03107 0.02082 -0.0345 0.0826 0.7415 8.500 0.8628 0.03187 0.02173 -0.0338 0.0756 0.7441 8.750 0.8847 0.03284 0.02276 -0.0333 0.0701 0.7470 9.000 0.9076 0.03371 0.02377 -0.0330 0.0639 0.7501 9.250 0.9306 0.03480 0.02488 -0.0328 0.0587 0.7535 9.500 0.9528 0.03572 0.02602 -0.0324 0.0526 0.7568 9.750 0.9718 0.03684 0.02719 -0.0318 0.0475 0.7602 10.000 0.9921 0.03785 0.02849 -0.0311 0.0419 0.7642 10.250 1.0079 0.03909 0.02970 -0.0303 0.0379 0.7687 10.500 1.0307 0.04059 0.03160 -0.0298 0.0335 0.7730 10.750 1.0439 0.04179 0.03291 -0.0286 0.0306 0.7782 11.000 1.0618 0.04366 0.03503 -0.0278 0.0281 0.7842 11.250 1.0779 0.04575 0.03756 -0.0267 0.0258 0.7899 11.500 1.0894 0.04780 0.03989 -0.0252 0.0244 0.7971 11.750 1.0972 0.04975 0.04207 -0.0235 0.0235 0.8048 12.000 1.1031 0.05200 0.04452 -0.0217 0.0228 0.8141 12.250 1.1028 0.05517 0.04812 -0.0193 0.0222 0.8242 12.500 1.0957 0.05874 0.05220 -0.0163 0.0218 0.8366 12.750 1.0827 0.06249 0.05642 -0.0132 0.0214 0.8541 13.000 1.0661 0.06608 0.06047 -0.0100 0.0213 0.8914 13.250 1.0455 0.07018 0.06492 -0.0077 0.0211 1.0000 13.500 1.0238 0.07531 0.07035 -0.0065 0.0210 1.0000 13.750 1.0001 0.08094 0.07625 -0.0063 0.0210 1.0000 14.000 0.9753 0.08714 0.08268 -0.0073 0.0211 1.0000 14.250 0.9481 0.09448 0.09023 -0.0099 0.0213 1.0000 14.500 0.9210 0.10308 0.09899 -0.0143 0.0216 1.0000 14.750 0.8933 0.11371 0.10974 -0.0211 0.0219 1.0000 15.000 0.8667 0.12677 0.12285 -0.0296 0.0223 1.0000