XFOIL Version 6.96 Calculated polar for: E230 (9.96%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -1.0547 0.03144 0.02622 0.0169 1.0000 0.0121 -9.250 -1.0382 0.02979 0.02436 0.0183 1.0000 0.0120 -9.000 -1.0207 0.02799 0.02236 0.0195 1.0000 0.0119 -8.750 -1.0020 0.02614 0.02031 0.0207 1.0000 0.0119 -8.500 -0.9834 0.02385 0.01783 0.0218 1.0000 0.0120 -8.250 -0.9650 0.02163 0.01547 0.0230 1.0000 0.0123 -8.000 -0.9451 0.02014 0.01389 0.0241 1.0000 0.0126 -7.750 -0.9243 0.01893 0.01258 0.0252 1.0000 0.0126 -7.500 -0.9038 0.01776 0.01133 0.0263 1.0000 0.0128 -7.250 -0.8828 0.01675 0.01025 0.0274 1.0000 0.0131 -7.000 -0.8611 0.01588 0.00931 0.0284 1.0000 0.0134 -6.750 -0.8386 0.01509 0.00846 0.0293 1.0000 0.0139 -6.500 -0.8155 0.01437 0.00768 0.0301 1.0000 0.0146 -6.250 -0.7916 0.01375 0.00698 0.0308 1.0000 0.0154 -6.000 -0.7671 0.01319 0.00635 0.0313 1.0000 0.0160 -5.750 -0.7433 0.01251 0.00561 0.0320 1.0000 0.0179 -5.500 -0.7179 0.01205 0.00512 0.0325 1.0000 0.0212 -5.250 -0.6966 0.01103 0.00440 0.0335 1.0000 0.0627 -5.000 -0.6740 0.01027 0.00395 0.0341 1.0000 0.1189 -4.750 -0.6501 0.00975 0.00364 0.0345 1.0000 0.1624 -4.500 -0.6271 0.00929 0.00338 0.0352 1.0000 0.2048 -4.250 -0.5942 0.00882 0.00313 0.0337 0.9870 0.2571 -4.000 -0.5598 0.00841 0.00292 0.0320 0.9745 0.3102 -3.750 -0.5310 0.00804 0.00276 0.0316 0.9601 0.3635 -3.500 -0.5089 0.00777 0.00265 0.0329 0.9443 0.4099 -3.250 -0.4885 0.00753 0.00253 0.0347 0.9291 0.4539 -3.000 -0.4674 0.00732 0.00242 0.0363 0.9150 0.4913 -2.750 -0.4455 0.00711 0.00231 0.0377 0.9017 0.5282 -2.500 -0.4229 0.00691 0.00219 0.0390 0.8885 0.5655 -2.250 -0.3998 0.00671 0.00208 0.0402 0.8752 0.6046 -2.000 -0.3765 0.00651 0.00199 0.0414 0.8619 0.6430 -1.750 -0.3526 0.00634 0.00191 0.0425 0.8485 0.6800 -1.500 -0.3286 0.00618 0.00183 0.0435 0.8349 0.7151 -1.250 -0.3040 0.00604 0.00177 0.0445 0.8209 0.7499 -0.750 -0.2533 0.00582 0.00170 0.0462 0.7922 0.8150 -0.500 -0.2265 0.00576 0.00168 0.0468 0.7772 0.8447 -0.250 -0.1982 0.00574 0.00168 0.0470 0.7617 0.8718 0.000 -0.1666 0.00576 0.00172 0.0466 0.7455 0.8936 0.250 -0.1330 0.00584 0.00177 0.0456 0.7285 0.9114 0.500 -0.0975 0.00596 0.00184 0.0443 0.7105 0.9245 0.750 -0.0621 0.00609 0.00192 0.0429 0.6910 0.9350 1.000 -0.0300 0.00624 0.00200 0.0423 0.6705 0.9452 1.250 0.0089 0.00643 0.00211 0.0401 0.6482 0.9500 1.500 0.0401 0.00661 0.00222 0.0396 0.6251 0.9585 1.750 0.0800 0.00679 0.00232 0.0372 0.6003 0.9615 2.000 0.1175 0.00698 0.00242 0.0352 0.5732 0.9661 2.500 0.1900 0.00735 0.00262 0.0318 0.5153 0.9753 2.750 0.2274 0.00754 0.00272 0.0297 0.4835 0.9796 3.000 0.2617 0.00776 0.00284 0.0283 0.4491 0.9845 3.250 0.3011 0.00796 0.00291 0.0257 0.4056 0.9871 3.500 0.3387 0.00821 0.00299 0.0234 0.3577 0.9904 3.750 0.3747 0.00851 0.00311 0.0214 0.3086 0.9940 4.000 0.4120 0.00882 0.00320 0.0190 0.2521 0.9965 4.250 0.4494 0.00914 0.00333 0.0166 0.2022 0.9993 4.500 0.4776 0.00948 0.00351 0.0161 0.1589 1.0000 5.250 0.5491 0.01110 0.00446 0.0172 0.0303 1.0000 5.500 0.5730 0.01157 0.00492 0.0178 0.0227 1.0000 5.750 0.5965 0.01209 0.00549 0.0185 0.0203 1.0000 6.000 0.6200 0.01253 0.00600 0.0192 0.0192 1.0000 6.250 0.6429 0.01304 0.00657 0.0200 0.0183 1.0000 6.500 0.6654 0.01363 0.00724 0.0208 0.0175 1.0000 6.750 0.6872 0.01433 0.00799 0.0217 0.0168 1.0000 7.000 0.7080 0.01516 0.00889 0.0227 0.0164 1.0000 7.250 0.7275 0.01622 0.01002 0.0239 0.0159 1.0000 7.500 0.7447 0.01781 0.01172 0.0253 0.0154 1.0000 7.750 0.7653 0.01857 0.01258 0.0265 0.0151 1.0000 8.000 0.7843 0.01974 0.01388 0.0278 0.0150 1.0000 8.250 0.8029 0.02097 0.01523 0.0291 0.0149 1.0000 8.500 0.8208 0.02233 0.01675 0.0305 0.0147 1.0000 8.750 0.8373 0.02393 0.01853 0.0320 0.0147 1.0000 9.000 0.8521 0.02580 0.02061 0.0337 0.0146 1.0000 9.250 0.8642 0.02802 0.02310 0.0355 0.0146 1.0000 9.500 0.8720 0.03077 0.02614 0.0376 0.0148 1.0000 9.750 0.8730 0.03545 0.03106 0.0397 0.0155 1.0000 10.000 0.8866 0.03618 0.03195 0.0414 0.0158 1.0000 11.750 0.6302 0.10286 0.10050 0.0180 0.0286 1.0000 12.000 0.6297 0.10693 0.10456 0.0165 0.0283 1.0000