XFOIL Version 6.96 Calculated polar for: NACA M20 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.000 -0.3616 0.09897 0.09585 0.0018 0.6656 0.0092 -7.750 -0.3567 0.09533 0.09221 -0.0004 0.6603 0.0093 -7.500 -0.3533 0.09155 0.08843 -0.0031 0.6550 0.0095 -7.250 -0.3471 0.08665 0.08350 -0.0075 0.6507 0.0098 -7.000 -0.3355 0.08284 0.07966 -0.0112 0.6456 0.0101 -6.750 -0.3201 0.08056 0.07735 -0.0134 0.6396 0.0104 -6.500 -0.3038 0.07795 0.07468 -0.0160 0.6342 0.0109 -6.250 -0.2869 0.07453 0.07123 -0.0194 0.6287 0.0116 -6.000 -0.2687 0.07039 0.06702 -0.0233 0.6237 0.0121 -5.750 -0.2468 0.06328 0.05978 -0.0299 0.6201 0.0132 -5.500 -0.2263 0.06145 0.05789 -0.0314 0.6144 0.0135 -5.250 -0.2045 0.05962 0.05599 -0.0330 0.6086 0.0140 -5.000 -0.1810 0.05689 0.05317 -0.0354 0.6034 0.0150 -4.750 -0.1554 0.05308 0.04924 -0.0383 0.5981 0.0159 -4.500 -0.1252 0.04755 0.04350 -0.0423 0.5936 0.0175 -4.250 -0.1027 0.04646 0.04236 -0.0429 0.5885 0.0180 -4.000 -0.0777 0.04463 0.04043 -0.0440 0.5828 0.0189 -3.750 -0.0506 0.04187 0.03752 -0.0455 0.5776 0.0196 -3.500 -0.0224 0.03890 0.03438 -0.0469 0.5726 0.0204 -3.250 0.0120 0.03425 0.02941 -0.0485 0.5679 0.0228 -3.000 0.0368 0.03223 0.02724 -0.0490 0.5629 0.0233 -2.750 0.0624 0.03089 0.02579 -0.0495 0.5580 0.0239 -2.500 0.0893 0.02912 0.02388 -0.0498 0.5526 0.0243 -2.250 0.1165 0.02756 0.02217 -0.0502 0.5473 0.0250 -2.000 0.1444 0.02593 0.02038 -0.0504 0.5422 0.0260 -1.750 0.1730 0.02361 0.01781 -0.0505 0.5372 0.0261 -1.500 0.2015 0.02150 0.01544 -0.0504 0.5327 0.0264 -1.250 0.2299 0.01956 0.01326 -0.0503 0.5283 0.0267 -1.000 0.2583 0.01773 0.01115 -0.0502 0.5233 0.0269 -0.750 0.2865 0.01635 0.00951 -0.0501 0.5183 0.0276 -0.500 0.3148 0.01496 0.00785 -0.0500 0.5136 0.0275 -0.250 0.3431 0.01393 0.00660 -0.0499 0.5086 0.0275 0.000 0.3714 0.01319 0.00568 -0.0499 0.5040 0.0278 0.250 0.3996 0.01263 0.00500 -0.0500 0.4997 0.0282 0.500 0.4278 0.01221 0.00449 -0.0500 0.4946 0.0288 0.750 0.4559 0.01191 0.00410 -0.0501 0.4896 0.0293 1.000 0.4839 0.01165 0.00378 -0.0502 0.4853 0.0297 1.250 0.5119 0.01143 0.00353 -0.0503 0.4808 0.0300 1.500 0.5398 0.01125 0.00331 -0.0503 0.4763 0.0302 1.750 0.5676 0.01112 0.00315 -0.0504 0.4720 0.0305 2.000 0.5949 0.01077 0.00279 -0.0504 0.4675 0.0318 2.250 0.6226 0.01063 0.00264 -0.0504 0.4631 0.0322 2.500 0.6503 0.01056 0.00255 -0.0505 0.4591 0.0324 2.750 0.6782 0.01049 0.00249 -0.0506 0.4553 0.0329 3.000 0.7061 0.01045 0.00245 -0.0507 0.4509 0.0336 3.250 0.7340 0.01046 0.00245 -0.0509 0.4466 0.0350 3.500 0.7618 0.01049 0.00247 -0.0510 0.4428 0.0371 3.750 0.7899 0.01050 0.00252 -0.0512 0.4383 0.0406 4.000 0.8176 0.01051 0.00261 -0.0514 0.4328 0.0680 4.250 0.8450 0.01051 0.00275 -0.0515 0.4267 0.1459 4.750 0.9259 0.00922 0.00317 -0.0579 0.4141 1.0000 5.250 0.9782 0.00946 0.00341 -0.0576 0.4039 1.0000 5.500 1.0041 0.00962 0.00356 -0.0574 0.3941 1.0000 5.750 1.0298 0.00981 0.00371 -0.0572 0.3840 1.0000 6.000 1.0552 0.01003 0.00388 -0.0571 0.3678 1.0000 6.250 1.0806 0.01027 0.00409 -0.0569 0.3522 1.0000 6.500 1.1049 0.01065 0.00437 -0.0567 0.3248 1.0000 6.750 1.1251 0.01165 0.00497 -0.0562 0.2540 1.0000 7.000 1.1379 0.01362 0.00630 -0.0550 0.1458 1.0000 7.500 1.1676 0.01645 0.00856 -0.0527 0.0197 1.0000 7.750 1.1894 0.01693 0.00910 -0.0521 0.0176 1.0000 8.000 1.2102 0.01750 0.00971 -0.0514 0.0155 1.0000 8.250 1.2290 0.01822 0.01049 -0.0505 0.0133 1.0000 8.500 1.2476 0.01891 0.01125 -0.0497 0.0123 1.0000 8.750 1.2656 0.01961 0.01204 -0.0487 0.0115 1.0000 9.000 1.2817 0.02041 0.01291 -0.0476 0.0108 1.0000 9.250 1.2958 0.02131 0.01387 -0.0463 0.0101 1.0000 9.500 1.3057 0.02232 0.01495 -0.0446 0.0096 1.0000 9.750 1.3086 0.02384 0.01654 -0.0426 0.0090 1.0000 10.000 1.3117 0.02574 0.01854 -0.0414 0.0086 1.0000 10.250 1.3199 0.02740 0.02030 -0.0408 0.0082 1.0000 10.500 1.3254 0.02941 0.02242 -0.0402 0.0080 1.0000 10.750 1.3296 0.03165 0.02475 -0.0398 0.0077 1.0000 11.000 1.3327 0.03402 0.02722 -0.0394 0.0074 1.0000 11.250 1.3348 0.03652 0.02980 -0.0390 0.0072 1.0000 11.500 1.3362 0.03912 0.03249 -0.0387 0.0070 1.0000 11.750 1.3370 0.04179 0.03524 -0.0383 0.0068 1.0000 12.000 1.3370 0.04456 0.03809 -0.0380 0.0066 1.0000 12.250 1.3363 0.04743 0.04103 -0.0377 0.0065 1.0000 12.500 1.3345 0.05041 0.04409 -0.0374 0.0063 1.0000 12.750 1.3311 0.05360 0.04737 -0.0372 0.0062 1.0000 13.000 1.3245 0.05714 0.05099 -0.0368 0.0060 1.0000 13.250 1.3238 0.06015 0.05409 -0.0367 0.0059 1.0000 13.500 1.3254 0.06296 0.05699 -0.0366 0.0057 1.0000 13.750 1.3266 0.06581 0.05993 -0.0365 0.0055 1.0000 14.000 1.3280 0.06865 0.06287 -0.0365 0.0054 1.0000 14.250 1.3290 0.07157 0.06588 -0.0364 0.0052 1.0000 14.500 1.3301 0.07445 0.06885 -0.0364 0.0051 1.0000 14.750 1.3312 0.07735 0.07184 -0.0363 0.0049 1.0000 15.000 1.3327 0.08022 0.07480 -0.0363 0.0048 1.0000 15.250 1.3341 0.08316 0.07783 -0.0364 0.0047 1.0000 15.500 1.3355 0.08613 0.08089 -0.0365 0.0046 1.0000 15.750 1.3367 0.08918 0.08404 -0.0368 0.0045 1.0000 16.000 1.3373 0.09235 0.08730 -0.0372 0.0044 1.0000 16.250 1.3378 0.09558 0.09063 -0.0377 0.0043 1.0000 16.500 1.3376 0.09897 0.09410 -0.0382 0.0043 1.0000 16.750 1.3371 0.10241 0.09764 -0.0389 0.0042 1.0000 17.000 1.3354 0.10606 0.10138 -0.0396 0.0041 1.0000 17.250 1.3327 0.10981 0.10525 -0.0403 0.0040 1.0000 17.500 1.3273 0.11398 0.10956 -0.0411 0.0040 1.0000 17.750 1.3224 0.11834 0.11407 -0.0422 0.0039 1.0000 18.000 1.3164 0.12306 0.11896 -0.0436 0.0039 1.0000 18.250 1.3089 0.12813 0.12421 -0.0454 0.0039 1.0000 18.500 1.3000 0.13361 0.12988 -0.0475 0.0038 1.0000 18.750 1.2893 0.13966 0.13611 -0.0501 0.0038 1.0000 19.000 1.2775 0.14619 0.14283 -0.0531 0.0038 1.0000 19.250 1.2645 0.15325 0.15009 -0.0568 0.0037 1.0000