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 = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -7.000 -0.3835 0.08360 0.08118 0.0242 0.6003 0.0031 -6.750 -0.3830 0.08005 0.07763 0.0227 0.5957 0.0032 -6.500 -0.3837 0.07654 0.07411 0.0211 0.5910 0.0033 -6.250 -0.3775 0.07257 0.07012 0.0188 0.5871 0.0034 -6.000 -0.3692 0.06855 0.06608 0.0165 0.5824 0.0034 -5.750 -0.3585 0.06440 0.06189 0.0141 0.5779 0.0035 -5.250 -0.3895 0.07244 0.06968 0.0147 0.5810 0.0035 -4.250 -0.2917 0.05805 0.05495 0.0046 0.5608 0.0036 -2.750 -0.1378 0.03883 0.03507 -0.0015 0.5314 0.0037 -2.500 -0.1125 0.03633 0.03246 -0.0019 0.5266 0.0038 -2.250 -0.0856 0.03392 0.02992 -0.0021 0.5216 0.0039 -2.000 -0.0578 0.03157 0.02742 -0.0022 0.5168 0.0041 -1.750 -0.0295 0.02923 0.02494 -0.0022 0.5122 0.0043 -1.500 -0.0008 0.02694 0.02248 -0.0019 0.5072 0.0044 -1.250 0.0282 0.02467 0.02002 -0.0015 0.5025 0.0048 -0.750 0.0870 0.01983 0.01476 -0.0001 0.4936 0.0045 -0.500 0.1168 0.01710 0.01172 0.0009 0.4888 0.0042 -0.250 0.1459 0.01524 0.00961 0.0016 0.4847 0.0046 0.000 0.1753 0.01371 0.00781 0.0023 0.4766 0.0054 0.250 0.2040 0.01240 0.00624 0.0026 0.4654 0.0052 0.500 0.2327 0.01130 0.00489 0.0029 0.4526 0.0050 0.750 0.2611 0.01043 0.00384 0.0032 0.4451 0.0048 1.000 0.2890 0.00973 0.00300 0.0035 0.4377 0.0048 1.250 0.3166 0.00922 0.00237 0.0037 0.4294 0.0052 1.500 0.3444 0.00895 0.00202 0.0038 0.4206 0.0058 1.750 0.3722 0.00879 0.00182 0.0038 0.4110 0.0072 2.000 0.4003 0.00868 0.00164 0.0037 0.3994 0.0081 2.250 0.4284 0.00864 0.00152 0.0036 0.3858 0.0090 2.500 0.4565 0.00859 0.00134 0.0035 0.3683 0.0124 2.750 0.4848 0.00866 0.00130 0.0032 0.3501 0.0148 3.000 0.5131 0.00882 0.00131 0.0029 0.3243 0.0211 3.250 0.5412 0.00914 0.00151 0.0024 0.2727 0.0601 3.500 0.5686 0.01087 0.00242 0.0008 0.0410 0.1412 3.750 0.5966 0.01100 0.00254 0.0006 0.0372 0.1560 4.000 0.6244 0.01106 0.00268 0.0003 0.0354 0.1918 4.250 0.6375 0.00941 0.00284 0.0032 0.0348 0.9528 4.500 0.6695 0.00959 0.00305 0.0021 0.0342 0.9783 4.750 0.7047 0.00981 0.00326 0.0002 0.0338 0.9881 5.000 0.7411 0.01004 0.00350 -0.0020 0.0334 0.9918 5.250 0.7725 0.01026 0.00373 -0.0031 0.0331 0.9936 5.500 0.8032 0.01050 0.00398 -0.0041 0.0328 0.9951 5.750 0.8358 0.01074 0.00424 -0.0055 0.0327 0.9960 6.000 0.8686 0.01100 0.00452 -0.0070 0.0326 0.9971 6.250 0.8995 0.01125 0.00479 -0.0081 0.0325 0.9979 6.500 0.9302 0.01151 0.00507 -0.0092 0.0324 0.9987 6.750 0.9607 0.01178 0.00538 -0.0102 0.0323 0.9995 7.000 0.9904 0.01206 0.00569 -0.0111 0.0322 1.0000 7.250 1.0152 0.01232 0.00598 -0.0109 0.0320 1.0000 7.500 1.0399 0.01259 0.00629 -0.0106 0.0317 1.0000 7.750 1.0645 0.01283 0.00657 -0.0104 0.0310 1.0000 8.000 1.0892 0.01301 0.00677 -0.0102 0.0290 1.0000 8.250 1.1138 0.01326 0.00703 -0.0100 0.0265 1.0000 8.500 1.1381 0.01358 0.00735 -0.0099 0.0229 1.0000 8.750 1.1622 0.01393 0.00774 -0.0097 0.0202 1.0000 9.000 1.1837 0.01489 0.00858 -0.0095 0.0043 1.0000 9.250 1.2061 0.01554 0.00930 -0.0093 0.0029 1.0000 9.500 1.2278 0.01625 0.01008 -0.0090 0.0022 1.0000 9.750 1.2495 0.01690 0.01081 -0.0086 0.0018 1.0000 10.000 1.2700 0.01764 0.01162 -0.0083 0.0015 1.0000 10.250 1.2889 0.01854 0.01262 -0.0078 0.0012 1.0000 10.500 1.3080 0.01934 0.01353 -0.0073 0.0011 1.0000 10.750 1.3256 0.02029 0.01457 -0.0068 0.0010 1.0000 11.000 1.3418 0.02133 0.01570 -0.0062 0.0009 1.0000 11.250 1.3563 0.02247 0.01694 -0.0056 0.0008 1.0000 11.500 1.3675 0.02390 0.01848 -0.0051 0.0007 1.0000 11.750 1.3698 0.02596 0.02066 -0.0047 0.0007 1.0000 12.000 1.3684 0.02866 0.02350 -0.0045 0.0006 1.0000 12.250 1.3737 0.03083 0.02578 -0.0045 0.0006 1.0000 12.500 1.3771 0.03325 0.02833 -0.0047 0.0006 1.0000 12.750 1.3789 0.03590 0.03110 -0.0049 0.0005 1.0000 13.000 1.3792 0.03875 0.03406 -0.0051 0.0005 1.0000 13.250 1.3782 0.04176 0.03720 -0.0054 0.0005 1.0000 13.500 1.3752 0.04504 0.04061 -0.0058 0.0005 1.0000 13.750 1.3711 0.04849 0.04419 -0.0063 0.0004 1.0000 14.000 1.3656 0.05216 0.04799 -0.0069 0.0004 1.0000 14.250 1.3591 0.05603 0.05199 -0.0076 0.0004 1.0000 14.500 1.3518 0.06007 0.05615 -0.0084 0.0004 1.0000 14.750 1.3439 0.06445 0.06068 -0.0096 0.0004 1.0000 15.000 1.3354 0.06905 0.06541 -0.0109 0.0004 1.0000 15.250 1.3263 0.07389 0.07038 -0.0124 0.0004 1.0000 15.500 1.3163 0.07903 0.07566 -0.0141 0.0004 1.0000 15.750 1.3054 0.08443 0.08119 -0.0159 0.0004 1.0000 16.000 1.2936 0.09014 0.08703 -0.0180 0.0004 1.0000 16.250 1.2813 0.09611 0.09313 -0.0203 0.0004 1.0000 16.500 1.2681 0.10233 0.09948 -0.0228 0.0004 1.0000 16.750 1.2539 0.10893 0.10621 -0.0255 0.0004 1.0000 17.000 1.2399 0.11571 0.11311 -0.0284 0.0004 1.0000 17.250 1.2249 0.12282 0.12034 -0.0315 0.0004 1.0000 17.500 1.2097 0.13021 0.12785 -0.0349 0.0004 1.0000 17.750 1.1947 0.13784 0.13560 -0.0385 0.0004 1.0000