XFOIL Version 6.94 Calculated polar for: NACA 63(2)-615 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 0.5039 0.00892 0.00342 -0.1138 0.6509 0.6390 0.500 0.5614 0.00899 0.00350 -0.1142 0.6453 0.6480 1.000 0.6179 0.00891 0.00350 -0.1145 0.6351 0.6659 1.500 0.6739 0.00900 0.00362 -0.1146 0.6234 0.6794 2.000 0.7299 0.00928 0.00381 -0.1147 0.6078 0.6914 2.500 0.7866 0.00948 0.00402 -0.1151 0.5973 0.7006 3.000 0.8413 0.00949 0.00418 -0.1150 0.5897 0.7194 3.500 0.8953 0.00961 0.00435 -0.1147 0.5774 0.7344 4.000 0.9470 0.00988 0.00446 -0.1139 0.5487 0.7465 4.500 0.9952 0.00984 0.00442 -0.1124 0.5193 0.7645 5.000 1.0416 0.01012 0.00469 -0.1107 0.4892 0.7807 5.500 1.0854 0.01055 0.00501 -0.1085 0.4551 0.7945 6.000 1.1308 0.01086 0.00558 -0.1067 0.4287 0.8126 6.500 1.1586 0.01153 0.00614 -0.1016 0.3763 0.8344 7.000 1.1666 0.01249 0.00687 -0.0930 0.3143 0.8560 7.500 1.1569 0.01352 0.00777 -0.0812 0.2596 0.8918 8.000 1.1414 0.01457 0.00873 -0.0691 0.2163 0.9838 8.500 1.1446 0.01691 0.01074 -0.0631 0.1486 1.0000 9.000 1.1483 0.01914 0.01277 -0.0572 0.1080 1.0000 9.500 1.1466 0.02189 0.01530 -0.0513 0.0696 1.0000 10.000 1.1429 0.02503 0.01832 -0.0459 0.0374 1.0000 10.500 1.1384 0.02859 0.02194 -0.0409 0.0202 1.0000 11.000 1.1521 0.03121 0.02469 -0.0381 0.0185 1.0000 11.500 1.1630 0.03423 0.02784 -0.0355 0.0168 1.0000 12.000 1.1734 0.03751 0.03123 -0.0333 0.0154 1.0000 12.500 1.1822 0.04113 0.03496 -0.0314 0.0143 1.0000 13.000 1.1906 0.04498 0.03895 -0.0299 0.0135 1.0000 13.500 1.1947 0.04948 0.04361 -0.0288 0.0130 1.0000 14.000 1.2020 0.05396 0.04827 -0.0280 0.0127 1.0000 14.500 1.2041 0.05933 0.05383 -0.0277 0.0124 1.0000 15.000 1.2121 0.06428 0.05905 -0.0276 0.0124 1.0000 15.500 1.2167 0.06988 0.06486 -0.0280 0.0122 1.0000 16.000 1.2198 0.07596 0.07115 -0.0290 0.0120 1.0000 16.500 1.2241 0.08214 0.07754 -0.0303 0.0118 1.0000 17.000 1.2205 0.08986 0.08551 -0.0326 0.0116 1.0000 17.500 1.2184 0.09767 0.09355 -0.0353 0.0114 1.0000 18.000 1.2078 0.10718 0.10334 -0.0393 0.0113 1.0000 18.500 1.1967 0.11703 0.11345 -0.0439 0.0112 1.0000 19.000 1.1757 0.12916 0.12587 -0.0503 0.0111 1.0000 19.500 1.1493 0.14289 0.13990 -0.0581 0.0111 1.0000 20.000 1.1128 0.15955 0.15688 -0.0680 0.0113 1.0000 20.500 0.9602 0.21155 0.20927 -0.0945 0.0126 1.0000 21.000 0.9472 0.22511 0.22279 -0.1006 0.0127 1.0000 21.500 0.9483 0.23408 0.23174 -0.1050 0.0124 1.0000 22.500 0.9612 0.24800 0.24569 -0.1123 0.0116 1.0000 23.000 0.9722 0.25257 0.25027 -0.1154 0.0107 1.0000 24.500 0.9832 0.27813 0.27576 -0.1270 0.0064 1.0000