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 = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4821 0.01042 0.00228 -0.0616 0.4424 0.0700 0.500 0.5314 0.01072 0.00236 -0.0603 0.4035 0.0739 2.000 0.7145 0.00946 0.00321 -0.0648 0.3504 1.0000 2.500 0.7635 0.00980 0.00350 -0.0635 0.3408 1.0000 3.000 0.8125 0.01014 0.00381 -0.0622 0.3294 1.0000 3.500 0.8619 0.01048 0.00415 -0.0611 0.3184 1.0000 4.000 0.9115 0.01079 0.00450 -0.0600 0.3057 1.0000 4.500 0.9607 0.01111 0.00481 -0.0589 0.2838 1.0000 5.000 1.0096 0.01148 0.00514 -0.0578 0.2397 1.0000 5.500 1.0388 0.01364 0.00648 -0.0540 0.0962 1.0000 6.000 1.0762 0.01510 0.00773 -0.0513 0.0565 1.0000 6.500 1.1160 0.01625 0.00899 -0.0489 0.0510 1.0000 7.000 1.1534 0.01746 0.01033 -0.0463 0.0459 1.0000 7.500 1.1814 0.01916 0.01217 -0.0424 0.0413 1.0000 8.000 1.2137 0.02030 0.01346 -0.0391 0.0371 1.0000 8.500 1.2255 0.02242 0.01570 -0.0330 0.0327 1.0000 9.000 1.2582 0.02343 0.01682 -0.0304 0.0270 1.0000 9.500 1.2830 0.02501 0.01853 -0.0271 0.0212 1.0000 10.000 1.3034 0.02700 0.02063 -0.0239 0.0171 1.0000 10.500 1.3118 0.03007 0.02381 -0.0204 0.0146 1.0000 11.000 1.3152 0.03397 0.02795 -0.0174 0.0135 1.0000 11.500 1.3194 0.03828 0.03246 -0.0157 0.0122 1.0000 12.000 1.3100 0.04448 0.03882 -0.0148 0.0110 1.0000 12.500 1.3049 0.05081 0.04544 -0.0149 0.0105 1.0000 13.000 1.2975 0.05789 0.05278 -0.0158 0.0100 1.0000 13.500 1.2880 0.06573 0.06088 -0.0175 0.0096 1.0000 14.000 1.2789 0.07409 0.06947 -0.0201 0.0092 1.0000 14.500 1.2683 0.08307 0.07867 -0.0234 0.0089 1.0000 15.000 1.2541 0.09287 0.08870 -0.0270 0.0086 1.0000 15.500 1.2314 0.10437 0.10046 -0.0316 0.0083 1.0000 16.000 1.2093 0.11677 0.11318 -0.0376 0.0082 1.0000 17.000 1.1602 0.14478 0.14179 -0.0531 0.0082 1.0000