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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.3968 0.11336 0.11099 0.0103 0.7063 0.0115 -8.750 -0.3915 0.10991 0.10751 0.0084 0.7003 0.0116 -8.500 -0.3878 0.10568 0.10327 0.0074 0.6942 0.0117 -8.250 -0.3807 0.10276 0.10032 0.0066 0.6879 0.0118 -8.000 -0.3735 0.09998 0.09754 0.0052 0.6819 0.0120 -7.750 -0.3663 0.09719 0.09473 0.0037 0.6756 0.0122 -7.500 -0.3593 0.09433 0.09186 0.0018 0.6698 0.0125 -7.250 -0.3529 0.09153 0.08904 -0.0004 0.6638 0.0130 -7.000 -0.3414 0.08817 0.08565 -0.0038 0.6583 0.0140 -6.750 -0.3241 0.08370 0.08114 -0.0107 0.6536 0.0147 -6.500 -0.3070 0.07937 0.07677 -0.0161 0.6484 0.0148 -6.250 -0.2890 0.07531 0.07264 -0.0201 0.6432 0.0148 -6.000 -0.2762 0.07030 0.06760 -0.0226 0.6384 0.0150 -5.750 -0.2603 0.06767 0.06493 -0.0237 0.6324 0.0153 -5.500 -0.2411 0.06513 0.06233 -0.0256 0.6268 0.0156 -5.250 -0.2200 0.06255 0.05970 -0.0278 0.6214 0.0162 -5.000 -0.1864 0.05902 0.05604 -0.0327 0.6161 0.0185 -4.750 -0.1582 0.05517 0.05205 -0.0361 0.6112 0.0187 -4.500 -0.1324 0.05154 0.04833 -0.0383 0.6059 0.0187 -4.250 -0.1124 0.04640 0.04307 -0.0403 0.6009 0.0191 -4.000 -0.0913 0.04470 0.04131 -0.0408 0.5954 0.0195 -3.750 -0.0672 0.04284 0.03940 -0.0418 0.5899 0.0201 -3.500 -0.0411 0.04073 0.03717 -0.0429 0.5845 0.0211 -3.250 -0.0046 0.03834 0.03459 -0.0443 0.5795 0.0234 -3.000 0.0241 0.03569 0.03180 -0.0451 0.5741 0.0236 -2.750 0.0523 0.03289 0.02881 -0.0456 0.5688 0.0236 -2.500 0.0754 0.02821 0.02392 -0.0462 0.5645 0.0244 -2.250 0.1011 0.02691 0.02254 -0.0465 0.5589 0.0249 -2.000 0.1275 0.02565 0.02116 -0.0468 0.5536 0.0254 -1.750 0.1549 0.02425 0.01966 -0.0470 0.5485 0.0263 -1.500 0.1836 0.02274 0.01800 -0.0470 0.5430 0.0284 -1.250 0.2153 0.02170 0.01675 -0.0466 0.5377 0.0301 -1.000 0.2419 0.01709 0.01167 -0.0461 0.5336 0.0310 -0.750 0.2691 0.01602 0.01048 -0.0462 0.5283 0.0318 -0.500 0.2967 0.01539 0.00976 -0.0464 0.5231 0.0325 -0.250 0.3247 0.01469 0.00898 -0.0465 0.5181 0.0335 0.000 0.3530 0.01399 0.00815 -0.0466 0.5127 0.0350 0.250 0.3817 0.01368 0.00772 -0.0466 0.5076 0.0378 0.500 0.4108 0.01396 0.00793 -0.0466 0.5027 0.0390 0.750 0.4387 0.01039 0.00388 -0.0460 0.4985 0.0323 1.000 0.4668 0.00999 0.00340 -0.0460 0.4935 0.0322 1.250 0.4950 0.00964 0.00302 -0.0461 0.4888 0.0322 1.500 0.5229 0.00938 0.00272 -0.0461 0.4839 0.0321 1.750 0.5508 0.00920 0.00249 -0.0462 0.4791 0.0325 2.000 0.5789 0.00901 0.00232 -0.0462 0.4751 0.0332 2.250 0.6069 0.00886 0.00215 -0.0463 0.4704 0.0334 2.500 0.6349 0.00879 0.00204 -0.0464 0.4656 0.0341 2.750 0.6631 0.00870 0.00196 -0.0466 0.4613 0.0355 3.000 0.6913 0.00866 0.00191 -0.0467 0.4561 0.0371 3.250 0.7195 0.00869 0.00190 -0.0469 0.4505 0.0384 3.500 0.7478 0.00866 0.00190 -0.0471 0.4463 0.0398 3.750 0.7761 0.00866 0.00191 -0.0473 0.4418 0.0469 4.000 0.8037 0.00852 0.00206 -0.0475 0.4371 0.1993 4.250 0.8451 0.00705 0.00232 -0.0510 0.4316 0.9958 4.500 0.8922 0.00719 0.00242 -0.0556 0.4251 1.0000 4.750 0.9184 0.00729 0.00249 -0.0554 0.4175 1.0000 5.000 0.9445 0.00739 0.00256 -0.0552 0.4098 1.0000 5.250 0.9706 0.00750 0.00266 -0.0550 0.4017 1.0000 5.500 0.9965 0.00765 0.00276 -0.0548 0.3914 1.0000 5.750 1.0226 0.00777 0.00286 -0.0547 0.3809 1.0000 6.000 1.0483 0.00795 0.00301 -0.0545 0.3663 1.0000 6.250 1.0737 0.00821 0.00318 -0.0543 0.3461 1.0000 6.500 1.0975 0.00877 0.00349 -0.0541 0.2993 1.0000 6.750 1.1116 0.01096 0.00482 -0.0532 0.1520 1.0000 7.000 1.1239 0.01308 0.00630 -0.0519 0.0244 1.0000 7.250 1.1466 0.01354 0.00679 -0.0513 0.0202 1.0000 7.500 1.1691 0.01401 0.00730 -0.0507 0.0178 1.0000 7.750 1.1919 0.01443 0.00774 -0.0502 0.0165 1.0000 8.000 1.2139 0.01491 0.00826 -0.0496 0.0153 1.0000 8.250 1.2339 0.01561 0.00901 -0.0488 0.0140 1.0000 8.500 1.2520 0.01647 0.00997 -0.0477 0.0132 1.0000 8.750 1.2726 0.01701 0.01055 -0.0471 0.0127 1.0000 9.000 1.2923 0.01762 0.01119 -0.0463 0.0120 1.0000 9.250 1.3109 0.01827 0.01189 -0.0455 0.0114 1.0000 9.500 1.3273 0.01906 0.01272 -0.0444 0.0108 1.0000 9.750 1.3402 0.02005 0.01377 -0.0430 0.0104 1.0000 10.000 1.3399 0.02165 0.01547 -0.0402 0.0099 1.0000 10.250 1.3291 0.02460 0.01857 -0.0380 0.0096 1.0000 10.500 1.3364 0.02640 0.02044 -0.0375 0.0095 1.0000 10.750 1.3450 0.02814 0.02226 -0.0371 0.0093 1.0000 11.000 1.3511 0.03019 0.02439 -0.0367 0.0091 1.0000 11.250 1.3554 0.03243 0.02670 -0.0363 0.0089 1.0000 11.500 1.3586 0.03478 0.02914 -0.0359 0.0087 1.0000 11.750 1.3611 0.03719 0.03162 -0.0354 0.0085 1.0000 12.000 1.3646 0.03951 0.03400 -0.0350 0.0083 1.0000 12.250 1.3686 0.04180 0.03635 -0.0347 0.0080 1.0000 12.500 1.3726 0.04407 0.03867 -0.0344 0.0078 1.0000 12.750 1.3760 0.04644 0.04110 -0.0341 0.0076 1.0000 13.000 1.3776 0.04897 0.04368 -0.0338 0.0074 1.0000 13.250 1.3771 0.05169 0.04645 -0.0334 0.0072 1.0000 13.500 1.3745 0.05460 0.04943 -0.0328 0.0071 1.0000 13.750 1.3675 0.05736 0.05224 -0.0305 0.0068 1.0000 14.000 1.3706 0.05958 0.05455 -0.0295 0.0067 1.0000 14.250 1.3750 0.06199 0.05705 -0.0294 0.0066 1.0000 14.500 1.3791 0.06439 0.05953 -0.0291 0.0065 1.0000 14.750 1.3828 0.06681 0.06204 -0.0288 0.0064 1.0000 15.000 1.3862 0.06929 0.06462 -0.0284 0.0063 1.0000 15.250 1.3891 0.07180 0.06723 -0.0279 0.0062 1.0000 15.500 1.3910 0.07448 0.07003 -0.0275 0.0061 1.0000 15.750 1.3918 0.07737 0.07304 -0.0271 0.0060 1.0000 16.000 1.3918 0.08045 0.07624 -0.0270 0.0059 1.0000 16.250 1.3898 0.08384 0.07977 -0.0269 0.0058 1.0000 16.500 1.3863 0.08757 0.08363 -0.0271 0.0057 1.0000 16.750 1.3809 0.09170 0.08791 -0.0277 0.0056 1.0000 17.000 1.3738 0.09621 0.09257 -0.0286 0.0055 1.0000 17.250 1.3651 0.10106 0.09757 -0.0298 0.0054 1.0000 17.500 1.3564 0.10605 0.10270 -0.0313 0.0054 1.0000 17.750 1.3488 0.11101 0.10777 -0.0333 0.0053 1.0000 18.000 1.3410 0.11611 0.11298 -0.0354 0.0052 1.0000 18.250 1.3320 0.12155 0.11854 -0.0377 0.0052 1.0000 18.500 1.3246 0.12678 0.12387 -0.0402 0.0051 1.0000 18.750 1.3154 0.13248 0.12968 -0.0430 0.0051 1.0000