XFOIL Version 6.94 Calculated polar for: Rhode St. Genese 30 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4905 0.01067 0.00251 -0.0632 0.5723 0.0850 0.500 0.5337 0.01119 0.00259 -0.0607 0.4695 0.1006 1.500 0.6623 0.01019 0.00342 -0.0652 0.4060 1.0000 2.000 0.7103 0.01065 0.00376 -0.0637 0.3890 1.0000 2.500 0.7584 0.01112 0.00411 -0.0622 0.3727 1.0000 3.000 0.8074 0.01156 0.00452 -0.0610 0.3600 1.0000 3.500 0.8565 0.01199 0.00495 -0.0599 0.3472 1.0000 4.000 0.9056 0.01241 0.00541 -0.0587 0.3347 1.0000 4.500 0.9541 0.01279 0.00587 -0.0575 0.3187 1.0000 5.000 1.0017 0.01313 0.00629 -0.0562 0.2971 1.0000 5.500 1.0491 0.01344 0.00670 -0.0548 0.2609 1.0000 6.000 1.0772 0.01553 0.00799 -0.0510 0.1140 1.0000 6.500 1.1107 0.01727 0.00946 -0.0478 0.0666 1.0000 7.000 1.1444 0.01880 0.01110 -0.0446 0.0582 1.0000 7.500 1.1669 0.02088 0.01329 -0.0400 0.0517 1.0000 8.000 1.1895 0.02252 0.01513 -0.0353 0.0463 1.0000 8.500 1.1956 0.02532 0.01803 -0.0290 0.0413 1.0000 9.000 1.2131 0.02754 0.02043 -0.0250 0.0353 1.0000 9.500 1.2228 0.03069 0.02378 -0.0209 0.0295 1.0000 10.000 1.2309 0.03426 0.02745 -0.0175 0.0250 1.0000 10.500 1.2446 0.03742 0.03088 -0.0153 0.0215 1.0000 11.000 1.2495 0.04198 0.03552 -0.0131 0.0193 1.0000 11.500 1.2576 0.04628 0.04018 -0.0119 0.0174 1.0000 12.000 1.2615 0.05132 0.04547 -0.0114 0.0160 1.0000 12.500 1.2615 0.05711 0.05143 -0.0116 0.0150 1.0000 13.000 1.2519 0.06488 0.05956 -0.0117 0.0143 1.0000 13.500 1.2376 0.07370 0.06882 -0.0138 0.0138 1.0000 14.000 1.2185 0.08395 0.07947 -0.0178 0.0132 1.0000 14.500 1.1918 0.09641 0.09233 -0.0233 0.0130 1.0000 15.000 1.1558 0.11167 0.10801 -0.0312 0.0131 1.0000 15.500 1.1152 0.12919 0.12588 -0.0412 0.0134 1.0000 16.000 1.0730 0.14893 0.14593 -0.0532 0.0137 1.0000 16.500 1.0280 0.17226 0.16945 -0.0670 0.0145 1.0000 17.000 0.7491 0.20987 0.20739 -0.0761 0.0308 1.0000 17.500 0.7535 0.21708 0.21462 -0.0796 0.0279 1.0000 18.000 0.7648 0.22271 0.22029 -0.0817 0.0265 1.0000 18.500 0.7751 0.23057 0.22818 -0.0834 0.0256 1.0000 19.000 0.7713 0.23985 0.23745 -0.0889 0.0252 1.0000 19.500 0.7713 0.24864 0.24625 -0.0939 0.0226 1.0000 20.000 0.7794 0.25532 0.25296 -0.0969 0.0206 1.0000 20.500 0.7905 0.26140 0.25908 -0.0989 0.0198 1.0000 21.000 0.7981 0.27037 0.26806 -0.1016 0.0192 1.0000 21.500 0.7965 0.27931 0.27701 -0.1070 0.0182 1.0000 22.000 0.8032 0.28696 0.28468 -0.1103 0.0158 1.0000 22.500 0.8105 0.29400 0.29176 -0.1133 0.0151 1.0000 23.000 0.8213 0.30176 0.29955 -0.1149 0.0144 1.0000 23.500 0.8214 0.31121 0.30900 -0.1200 0.0133 1.0000 24.000 0.8274 0.31913 0.31695 -0.1232 0.0125 1.0000 24.500 0.8336 0.32677 0.32463 -0.1263 0.0117 1.0000 25.000 0.8401 0.33394 0.33183 -0.1292 0.0112 1.0000 25.500 0.8460 0.34259 0.34050 -0.1319 0.0108 1.0000 26.000 0.8495 0.35191 0.34984 -0.1358 0.0101 1.0000 26.500 0.8549 0.36016 0.35812 -0.1389 0.0089 1.0000 27.000 0.8598 0.36765 0.36565 -0.1419 0.0086 1.0000 27.500 0.8650 0.37521 0.37324 -0.1447 0.0083 1.0000 28.000 0.8684 0.38487 0.38291 -0.1481 0.0081 1.0000 28.500 0.8725 0.39364 0.39172 -0.1512 0.0078 1.0000 29.000 0.8765 0.40225 0.40035 -0.1542 0.0070 1.0000 29.500 0.8802 0.41039 0.40853 -0.1573 0.0066 1.0000 30.000 0.8833 0.41790 0.41608 -0.1602 0.0064 1.0000 31.000 0.8892 0.43617 0.43439 -0.1662 0.0059 1.0000 31.500 0.8915 0.44450 0.44276 -0.1691 0.0054 1.0000 32.000 0.8938 0.45288 0.45117 -0.1721 0.0051 1.0000 32.500 0.8956 0.46070 0.45902 -0.1750 0.0051 1.0000 33.000 0.8966 0.46820 0.46655 -0.1778 0.0047 1.0000 34.000 0.8987 0.48496 0.48337 -0.1836 0.0046 1.0000 34.500 0.8996 0.49346 0.49190 -0.1864 0.0045 1.0000 35.000 0.9000 0.50126 0.49974 -0.1892 0.0045 1.0000 35.500 0.9002 0.50937 0.50788 -0.1920 0.0042 1.0000 36.000 0.9001 0.51742 0.51597 -0.1947 0.0038 1.0000 36.500 0.8995 0.52471 0.52329 -0.1975 0.0039 1.0000 37.000 0.8982 0.53175 0.53037 -0.2001 0.0036 1.0000 37.500 0.8968 0.53900 0.53765 -0.2029 0.0034 1.0000