XFOIL Version 6.96 Calculated polar for: NACA M7 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 ------ -------- --------- --------- -------- -------- -------- -7.250 -0.4967 0.10165 0.09884 0.0369 0.6722 0.0040 -7.000 -0.4914 0.09839 0.09556 0.0345 0.6658 0.0041 -6.750 -0.4816 0.09485 0.09200 0.0316 0.6598 0.0042 -6.500 -0.4701 0.09128 0.08839 0.0287 0.6535 0.0043 -6.250 -0.4569 0.08767 0.08474 0.0257 0.6477 0.0044 -6.000 -0.4421 0.08403 0.08105 0.0227 0.6417 0.0046 -5.750 -0.4255 0.08038 0.07734 0.0198 0.6358 0.0048 -5.500 -0.4070 0.07673 0.07362 0.0169 0.6302 0.0052 -5.250 -0.3844 0.07317 0.06999 0.0137 0.6243 0.0055 -4.750 -0.3304 0.06642 0.06303 0.0068 0.6134 0.0057 -1.000 0.0665 0.02430 0.01871 -0.0016 0.5336 0.0089 -0.500 0.1216 0.01901 0.01288 -0.0006 0.5239 0.0100 -0.250 0.1493 0.01787 0.01156 -0.0006 0.5186 0.0116 0.250 0.2090 0.01435 0.00741 0.0009 0.5088 0.0080 0.500 0.2379 0.01310 0.00589 0.0012 0.5036 0.0075 0.750 0.2665 0.01214 0.00474 0.0016 0.4967 0.0072 1.000 0.2946 0.01143 0.00385 0.0018 0.4860 0.0073 1.250 0.3223 0.01091 0.00320 0.0021 0.4743 0.0079 1.500 0.3497 0.01051 0.00272 0.0023 0.4648 0.0098 1.750 0.3769 0.01015 0.00230 0.0024 0.4575 0.0106 2.000 0.4047 0.00994 0.00203 0.0025 0.4493 0.0118 2.250 0.4326 0.00985 0.00185 0.0025 0.4404 0.0146 2.500 0.4608 0.00982 0.00169 0.0024 0.4301 0.0174 2.750 0.4889 0.00978 0.00165 0.0023 0.4212 0.0328 3.000 0.5166 0.00970 0.00171 0.0022 0.4108 0.1208 3.250 0.5446 0.00974 0.00177 0.0019 0.3973 0.1653 3.750 0.6181 0.00832 0.00212 -0.0025 0.3628 0.9904 4.250 0.7029 0.00936 0.00262 -0.0102 0.2575 0.9994 4.500 0.7335 0.01150 0.00374 -0.0129 0.0478 1.0000 4.750 0.7591 0.01172 0.00394 -0.0128 0.0423 1.0000 5.000 0.7847 0.01193 0.00416 -0.0126 0.0412 1.0000 5.250 0.8101 0.01214 0.00438 -0.0123 0.0405 1.0000 5.500 0.8355 0.01237 0.00463 -0.0121 0.0399 1.0000 5.750 0.8608 0.01262 0.00490 -0.0119 0.0394 1.0000 6.000 0.8860 0.01289 0.00522 -0.0118 0.0389 1.0000 6.250 0.9110 0.01317 0.00554 -0.0116 0.0384 1.0000 6.500 0.9360 0.01349 0.00590 -0.0114 0.0380 1.0000 6.750 0.9608 0.01383 0.00631 -0.0112 0.0375 1.0000 7.000 0.9854 0.01420 0.00674 -0.0110 0.0370 1.0000 7.250 1.0098 0.01462 0.00723 -0.0108 0.0364 1.0000 7.500 1.0339 0.01508 0.00776 -0.0107 0.0357 1.0000 7.750 1.0575 0.01562 0.00839 -0.0105 0.0349 1.0000 8.000 1.0804 0.01628 0.00915 -0.0103 0.0339 1.0000 8.250 1.1024 0.01705 0.01002 -0.0100 0.0326 1.0000 8.500 1.1274 0.01705 0.01005 -0.0098 0.0314 1.0000 8.750 1.1518 0.01722 0.01029 -0.0096 0.0288 1.0000 9.000 1.1757 0.01747 0.01057 -0.0094 0.0246 1.0000 9.250 1.1988 0.01784 0.01094 -0.0092 0.0173 1.0000 9.500 1.2153 0.01926 0.01226 -0.0088 0.0049 1.0000 9.750 1.2318 0.02051 0.01363 -0.0082 0.0036 1.0000 10.000 1.2493 0.02152 0.01477 -0.0076 0.0031 1.0000 10.250 1.2647 0.02267 0.01606 -0.0069 0.0027 1.0000 10.500 1.2772 0.02406 0.01759 -0.0062 0.0024 1.0000 10.750 1.2853 0.02585 0.01957 -0.0056 0.0022 1.0000 11.000 1.2900 0.02768 0.02153 -0.0050 0.0021 1.0000 11.250 1.2947 0.02964 0.02362 -0.0046 0.0019 1.0000 11.500 1.2993 0.03180 0.02590 -0.0045 0.0017 1.0000 11.750 1.3035 0.03408 0.02829 -0.0045 0.0015 1.0000 12.000 1.3052 0.03669 0.03102 -0.0046 0.0014 1.0000 12.250 1.3039 0.03971 0.03415 -0.0048 0.0014 1.0000 12.500 1.2995 0.04312 0.03769 -0.0051 0.0013 1.0000 12.750 1.2939 0.04671 0.04140 -0.0055 0.0013 1.0000 13.000 1.2917 0.04994 0.04477 -0.0058 0.0012 1.0000 13.250 1.2885 0.05333 0.04830 -0.0062 0.0012 1.0000 13.500 1.2839 0.05696 0.05207 -0.0068 0.0012 1.0000 13.750 1.2782 0.06076 0.05601 -0.0074 0.0011 1.0000 14.000 1.2721 0.06476 0.06015 -0.0082 0.0011 1.0000 14.250 1.2656 0.06900 0.06453 -0.0092 0.0011 1.0000 14.500 1.2585 0.07349 0.06917 -0.0104 0.0010 1.0000 14.750 1.2507 0.07824 0.07407 -0.0119 0.0010 1.0000 15.000 1.2420 0.08324 0.07923 -0.0135 0.0010 1.0000 15.250 1.2326 0.08853 0.08466 -0.0153 0.0010 1.0000 15.500 1.2226 0.09410 0.09039 -0.0174 0.0010 1.0000 15.750 1.2118 0.09992 0.09636 -0.0196 0.0010 1.0000 16.000 1.2002 0.10610 0.10268 -0.0222 0.0010 1.0000 16.250 1.1881 0.11257 0.10930 -0.0250 0.0010 1.0000 16.500 1.1757 0.11925 0.11611 -0.0279 0.0010 1.0000 16.750 1.1628 0.12628 0.12329 -0.0312 0.0010 1.0000 17.000 1.1502 0.13351 0.13065 -0.0346 0.0010 1.0000