XFOIL Version 6.94 Calculated polar for: USA 27 mod. AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4823 0.01100 0.00319 -0.0855 0.5861 0.0462 0.500 0.5255 0.01100 0.00306 -0.0827 0.5509 0.0539 1.000 0.5603 0.01065 0.00317 -0.0785 0.5055 0.2572 1.500 0.6002 0.01089 0.00335 -0.0753 0.4647 0.3268 2.000 0.6417 0.01103 0.00352 -0.0726 0.4376 0.3994 3.000 0.8946 0.01148 0.00498 -0.1037 0.3917 1.0000 3.500 0.9298 0.01181 0.00514 -0.0997 0.3686 1.0000 4.000 0.9654 0.01208 0.00531 -0.0958 0.3497 1.0000 4.500 0.9949 0.01251 0.00554 -0.0907 0.3214 1.0000 5.000 1.0260 0.01286 0.00579 -0.0859 0.3032 1.0000 5.500 1.0463 0.01332 0.00606 -0.0789 0.2702 1.0000 6.000 1.0660 0.01391 0.00646 -0.0720 0.2357 1.0000 6.500 1.0666 0.01563 0.00758 -0.0622 0.1518 1.0000 7.000 1.0908 0.01656 0.00838 -0.0568 0.1263 1.0000 7.500 1.0802 0.01944 0.01069 -0.0463 0.0051 1.0000 8.000 1.1116 0.02038 0.01168 -0.0428 0.0047 1.0000 8.500 1.1422 0.02146 0.01283 -0.0394 0.0045 1.0000 9.000 1.1711 0.02272 0.01419 -0.0360 0.0045 1.0000 9.500 1.1980 0.02420 0.01580 -0.0327 0.0046 1.0000 10.000 1.2221 0.02597 0.01770 -0.0294 0.0046 1.0000 10.500 1.2426 0.02812 0.02001 -0.0261 0.0047 1.0000 11.000 1.2587 0.03075 0.02282 -0.0228 0.0049 1.0000 11.500 1.2692 0.03405 0.02631 -0.0197 0.0050 1.0000 12.000 1.2719 0.03836 0.03083 -0.0170 0.0051 1.0000 12.500 1.2667 0.04402 0.03672 -0.0150 0.0052 1.0000 13.000 1.2539 0.05117 0.04411 -0.0142 0.0053 1.0000 13.500 1.2513 0.05759 0.05072 -0.0142 0.0054 1.0000 14.000 1.2441 0.06485 0.05818 -0.0147 0.0056 1.0000 14.500 1.2307 0.07331 0.06688 -0.0159 0.0057 1.0000 15.000 1.2113 0.08287 0.07666 -0.0177 0.0059 1.0000 15.500 1.1916 0.09271 0.08672 -0.0198 0.0061 1.0000 16.000 1.1727 0.10254 0.09674 -0.0222 0.0063 1.0000 16.500 1.1581 0.11178 0.10613 -0.0245 0.0065 1.0000 17.000 1.1500 0.11978 0.11422 -0.0266 0.0067 1.0000 17.500 1.1544 0.12526 0.11969 -0.0275 0.0071 1.0000 18.000 1.1609 0.13188 0.12652 -0.0299 0.0076 1.0000 18.500 1.2006 0.12960 0.12406 -0.0261 0.0090 1.0000 19.000 1.2378 0.12943 0.12398 -0.0238 0.0113 1.0000 19.500 0.8861 0.13806 0.13368 -0.0155 0.0072 1.0000 20.000 0.8969 0.14052 0.13631 -0.0163 0.0082 1.0000 20.500 0.9276 0.13943 0.13524 -0.0148 0.0095 1.0000