XFOIL Version 6.96 Calculated polar for: M6 (65%) 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 ------ -------- --------- --------- -------- -------- -------- -9.250 -0.4625 0.08014 0.07859 -0.0120 1.0000 0.0126 -9.000 -0.4679 0.07519 0.07365 -0.0138 1.0000 0.0128 -8.750 -0.4767 0.06952 0.06801 -0.0163 1.0000 0.0138 -8.500 -0.4865 0.06438 0.06288 -0.0188 1.0000 0.0137 -8.250 -0.5049 0.05899 0.05751 -0.0230 1.0000 0.0136 -8.000 -0.5237 0.05480 0.05330 -0.0235 1.0000 0.0132 -7.750 -0.5364 0.04924 0.04768 -0.0245 1.0000 0.0135 -7.250 -0.6359 0.03775 0.03533 -0.0185 1.0000 0.0100 -7.000 -0.6934 0.01921 0.01514 -0.0054 1.0000 0.0094 -6.750 -0.6803 0.01713 0.01272 -0.0026 1.0000 0.0096 -6.500 -0.6625 0.01608 0.01150 -0.0006 1.0000 0.0099 -6.250 -0.6453 0.01492 0.01015 0.0015 1.0000 0.0102 -6.000 -0.6257 0.01437 0.00949 0.0032 1.0000 0.0106 -5.750 -0.5959 0.01252 0.00738 0.0025 0.9980 0.0114 -5.500 -0.5615 0.01195 0.00676 0.0009 0.9955 0.0121 -5.250 -0.5276 0.01159 0.00637 -0.0005 0.9926 0.0131 -5.000 -0.4942 0.01115 0.00587 -0.0018 0.9887 0.0141 -4.750 -0.4607 0.01036 0.00499 -0.0031 0.9848 0.0155 -4.500 -0.4282 0.01005 0.00469 -0.0042 0.9791 0.0170 -4.250 -0.3935 0.00981 0.00445 -0.0057 0.9730 0.0186 -4.000 -0.3570 0.00967 0.00429 -0.0076 0.9660 0.0197 -3.750 -0.3214 0.00892 0.00350 -0.0094 0.9559 0.0221 -3.500 -0.2854 0.00866 0.00321 -0.0112 0.9394 0.0239 -3.250 -0.2533 0.00848 0.00297 -0.0121 0.9153 0.0258 -3.000 -0.2261 0.00839 0.00278 -0.0118 0.8891 0.0267 -2.750 -0.2032 0.00798 0.00221 -0.0106 0.8635 0.0298 -2.500 -0.1789 0.00782 0.00196 -0.0096 0.8401 0.0326 -2.250 -0.1541 0.00772 0.00177 -0.0089 0.8183 0.0355 -2.000 -0.1295 0.00759 0.00155 -0.0080 0.7978 0.0399 -1.750 -0.1046 0.00748 0.00139 -0.0073 0.7798 0.0466 -1.500 -0.0803 0.00727 0.00126 -0.0065 0.7628 0.0808 -1.250 -0.0567 0.00698 0.00116 -0.0057 0.7466 0.1491 -1.000 -0.0335 0.00669 0.00107 -0.0048 0.7313 0.2307 -0.750 -0.0126 0.00619 0.00098 -0.0035 0.7171 0.3735 -0.500 -0.0031 0.00509 0.00085 0.0002 0.7040 0.6769 -0.250 0.0105 0.00443 0.00087 0.0037 0.6918 0.8779 0.000 0.0673 0.00448 0.00100 -0.0026 0.6788 0.9341 0.250 0.1132 0.00468 0.00114 -0.0065 0.6655 0.9524 0.500 0.1448 0.00485 0.00125 -0.0071 0.6516 0.9608 0.750 0.1828 0.00509 0.00141 -0.0091 0.6361 0.9680 1.000 0.2248 0.00535 0.00159 -0.0121 0.6183 0.9741 1.250 0.2736 0.00563 0.00180 -0.0166 0.6025 0.9794 1.500 0.3087 0.00581 0.00194 -0.0181 0.5883 0.9844 1.750 0.3478 0.00588 0.00194 -0.0206 0.5692 0.9859 2.000 0.3811 0.00593 0.00194 -0.0218 0.5524 0.9872 2.250 0.4133 0.00600 0.00194 -0.0229 0.5320 0.9887 2.500 0.4443 0.00612 0.00195 -0.0237 0.4995 0.9904 2.750 0.4741 0.00630 0.00197 -0.0243 0.4581 0.9924 3.000 0.5028 0.00653 0.00204 -0.0246 0.4146 0.9942 3.250 0.5334 0.00679 0.00208 -0.0255 0.3577 0.9954 3.500 0.5631 0.00717 0.00217 -0.0263 0.2853 0.9967 3.750 0.5923 0.00764 0.00232 -0.0270 0.2089 0.9981 4.000 0.6209 0.00820 0.00254 -0.0276 0.1311 0.9994 4.250 0.6457 0.00878 0.00282 -0.0274 0.0659 1.0000 4.500 0.6666 0.00923 0.00309 -0.0262 0.0313 1.0000 4.750 0.6887 0.00954 0.00338 -0.0251 0.0232 1.0000 5.000 0.7109 0.00982 0.00366 -0.0240 0.0203 1.0000 5.250 0.7321 0.01027 0.00419 -0.0227 0.0182 1.0000 5.500 0.7544 0.01053 0.00447 -0.0216 0.0175 1.0000 5.750 0.7761 0.01087 0.00486 -0.0205 0.0171 1.0000 6.000 0.7978 0.01120 0.00523 -0.0193 0.0164 1.0000 6.250 0.8190 0.01160 0.00569 -0.0181 0.0158 1.0000 6.500 0.8396 0.01207 0.00620 -0.0167 0.0155 1.0000 6.750 0.8598 0.01257 0.00676 -0.0154 0.0153 1.0000 7.000 0.8795 0.01312 0.00737 -0.0139 0.0150 1.0000 7.250 0.8990 0.01368 0.00799 -0.0124 0.0147 1.0000 7.500 0.9177 0.01433 0.00869 -0.0108 0.0144 1.0000 7.750 0.9356 0.01508 0.00950 -0.0091 0.0141 1.0000 8.000 0.9527 0.01597 0.01045 -0.0073 0.0140 1.0000 8.250 0.9653 0.01764 0.01223 -0.0048 0.0134 1.0000 8.500 0.9811 0.01896 0.01369 -0.0029 0.0130 1.0000 8.750 1.0018 0.01919 0.01399 -0.0017 0.0127 1.0000 9.000 1.0197 0.02001 0.01491 -0.0001 0.0124 1.0000 9.250 1.0374 0.02076 0.01575 0.0015 0.0119 1.0000 9.500 1.0537 0.02175 0.01685 0.0032 0.0116 1.0000 9.750 1.0701 0.02256 0.01775 0.0049 0.0112 1.0000 10.000 1.0855 0.02350 0.01879 0.0067 0.0109 1.0000 10.250 1.0994 0.02454 0.01995 0.0086 0.0107 1.0000 10.500 1.1142 0.02519 0.02066 0.0103 0.0103 1.0000 10.750 1.1265 0.02615 0.02169 0.0123 0.0100 1.0000 11.000 1.1243 0.02930 0.02508 0.0157 0.0095 1.0000 11.250 1.1263 0.03108 0.02710 0.0188 0.0092 1.0000 11.500 1.1340 0.03202 0.02817 0.0213 0.0090 1.0000 11.750 1.1339 0.03311 0.02939 0.0250 0.0088 1.0000 12.000 1.1364 0.03386 0.03024 0.0280 0.0084 1.0000 12.250 1.1365 0.03514 0.03163 0.0305 0.0082 1.0000 12.500 1.1404 0.03618 0.03275 0.0322 0.0079 1.0000 12.750 1.1324 0.03882 0.03556 0.0337 0.0078 1.0000 13.000 1.1256 0.04160 0.03849 0.0343 0.0077 1.0000 13.250 1.1163 0.04503 0.04207 0.0340 0.0076 1.0000 13.500 1.1184 0.04724 0.04436 0.0333 0.0074 1.0000 13.750 1.1121 0.05085 0.04809 0.0319 0.0073 1.0000 14.000 1.0869 0.05772 0.05518 0.0287 0.0074 1.0000 14.250 1.0759 0.06287 0.06045 0.0257 0.0073 1.0000 14.750 0.7583 0.10206 0.10030 0.0107 0.0095 1.0000 15.000 0.7461 0.10897 0.10728 0.0074 0.0096 1.0000