XFOIL Version 6.96 Calculated polar for: GOE 601 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -1.0232 0.08908 0.08569 -0.0717 1.0000 0.0166 -19.500 -1.0430 0.08287 0.07937 -0.0747 1.0000 0.0167 -19.250 -1.0595 0.07724 0.07365 -0.0775 1.0000 0.0169 -19.000 -1.0777 0.07147 0.06777 -0.0802 1.0000 0.0169 -18.750 -1.0885 0.06689 0.06312 -0.0823 1.0000 0.0173 -18.500 -1.1005 0.06229 0.05843 -0.0843 1.0000 0.0174 -18.250 -1.1106 0.05813 0.05419 -0.0859 1.0000 0.0176 -18.000 -1.1200 0.05425 0.05022 -0.0873 1.0000 0.0178 -17.750 -1.1299 0.05051 0.04638 -0.0884 1.0000 0.0178 -17.500 -1.1342 0.04755 0.04336 -0.0890 1.0000 0.0183 -17.250 -1.1408 0.04443 0.04016 -0.0896 1.0000 0.0184 -17.000 -1.1437 0.04181 0.03747 -0.0898 1.0000 0.0187 -16.750 -1.1482 0.03914 0.03472 -0.0899 1.0000 0.0189 -16.500 -1.1512 0.03678 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0.5199 2.500 0.4832 0.00872 0.00226 -0.0479 0.3470 0.5270 2.750 0.5004 0.00888 0.00236 -0.0457 0.3291 0.5362 3.000 0.5169 0.00904 0.00248 -0.0434 0.3114 0.5466 3.250 0.5357 0.00913 0.00258 -0.0416 0.3009 0.5621 3.500 0.5532 0.00922 0.00271 -0.0395 0.2911 0.5872 3.750 0.5713 0.00923 0.00285 -0.0376 0.2842 0.6283 4.000 0.5902 0.00928 0.00298 -0.0358 0.2786 0.6603 4.250 0.6083 0.00937 0.00313 -0.0338 0.2722 0.6876 4.500 0.6271 0.00941 0.00327 -0.0320 0.2672 0.7205 4.750 0.6439 0.00948 0.00343 -0.0298 0.2596 0.7542 5.000 0.6593 0.00952 0.00360 -0.0273 0.2539 0.7976 5.250 0.6755 0.00952 0.00376 -0.0248 0.2486 0.8491 5.500 0.7022 0.00959 0.00399 -0.0248 0.2418 0.9065 5.750 0.7645 0.00988 0.00431 -0.0327 0.2305 0.9427 6.000 0.8250 0.01025 0.00462 -0.0402 0.2176 0.9586 6.250 0.8685 0.01060 0.00490 -0.0440 0.2051 0.9705 6.500 0.9008 0.01093 0.00518 -0.0454 0.1931 0.9811 6.750 0.9286 0.01130 0.00547 -0.0459 0.1788 0.9895 7.000 0.9488 0.01181 0.00587 -0.0449 0.1585 0.9992 7.250 0.9596 0.01246 0.00634 -0.0422 0.1288 1.0000 7.500 0.9433 0.01394 0.00740 -0.0348 0.0571 1.0000 7.750 0.9507 0.01466 0.00800 -0.0315 0.0352 1.0000 8.000 0.9660 0.01507 0.00839 -0.0295 0.0319 1.0000 8.250 0.9825 0.01545 0.00878 -0.0278 0.0305 1.0000 8.500 0.9989 0.01586 0.00919 -0.0262 0.0294 1.0000 8.750 1.0152 0.01629 0.00963 -0.0245 0.0284 1.0000 9.000 1.0314 0.01675 0.01009 -0.0229 0.0276 1.0000 9.250 1.0479 0.01722 0.01058 -0.0214 0.0270 1.0000 9.500 1.0648 0.01768 0.01106 -0.0201 0.0266 1.0000 9.750 1.0813 0.01818 0.01157 -0.0187 0.0261 1.0000 10.000 1.0976 0.01871 0.01212 -0.0173 0.0257 1.0000 10.250 1.1134 0.01928 0.01272 -0.0160 0.0251 1.0000 10.500 1.1289 0.01990 0.01335 -0.0146 0.0247 1.0000 10.750 1.1440 0.02054 0.01402 -0.0133 0.0243 1.0000 11.000 1.1586 0.02125 0.01474 -0.0120 0.0239 1.0000 11.250 1.1722 0.02203 0.01556 -0.0106 0.0235 1.0000 11.500 1.1851 0.02288 0.01644 -0.0092 0.0231 1.0000 11.750 1.1986 0.02371 0.01730 -0.0080 0.0228 1.0000 12.000 1.2129 0.02450 0.01813 -0.0068 0.0227 1.0000 12.250 1.2267 0.02534 0.01901 -0.0057 0.0224 1.0000 12.500 1.2398 0.02624 0.01995 -0.0046 0.0222 1.0000 12.750 1.2527 0.02718 0.02092 -0.0036 0.0219 1.0000 13.000 1.2653 0.02815 0.02193 -0.0025 0.0215 1.0000 13.250 1.2766 0.02924 0.02307 -0.0015 0.0213 1.0000 13.500 1.2885 0.03030 0.02416 -0.0005 0.0209 1.0000 13.750 1.2990 0.03150 0.02540 0.0005 0.0206 1.0000 14.000 1.3089 0.03277 0.02671 0.0015 0.0204 1.0000 14.250 1.3177 0.03415 0.02814 0.0024 0.0201 1.0000 14.500 1.3251 0.03568 0.02972 0.0034 0.0199 1.0000 14.750 1.3315 0.03735 0.03144 0.0043 0.0196 1.0000 15.000 1.3346 0.03935 0.03350 0.0052 0.0192 1.0000 15.250 1.3408 0.04112 0.03533 0.0059 0.0191 1.0000 15.500 1.3484 0.04281 0.03708 0.0064 0.0189 1.0000 15.750 1.3548 0.04466 0.03899 0.0069 0.0188 1.0000 16.000 1.3611 0.04656 0.04096 0.0073 0.0186 1.0000 16.250 1.3666 0.04859 0.04305 0.0076 0.0183 1.0000 16.500 1.3712 0.05075 0.04528 0.0079 0.0180 1.0000 16.750 1.3740 0.05315 0.04775 0.0080 0.0179 1.0000 17.000 1.3763 0.05567 0.05034 0.0081 0.0177 1.0000 17.250 1.3773 0.05841 0.05315 0.0080 0.0175 1.0000 17.500 1.3780 0.06123 0.05604 0.0078 0.0173 1.0000 17.750 1.3782 0.06416 0.05904 0.0075 0.0171 1.0000 18.000 1.3751 0.06756 0.06252 0.0071 0.0170 1.0000 18.250 1.3724 0.07099 0.06603 0.0065 0.0168 1.0000 18.500 1.3684 0.07466 0.06978 0.0058 0.0166 1.0000 18.750 1.3627 0.07860 0.07380 0.0048 0.0164 1.0000 19.000 1.3564 0.08270 0.07797 0.0038 0.0161 1.0000 19.250 1.3445 0.08771 0.08309 0.0023 0.0162 1.0000