XFOIL Version 6.94 Calculated polar for: AG37 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 0.3793 0.00649 0.00146 -0.0447 0.6038 1.0000 0.500 0.4337 0.00687 0.00161 -0.0444 0.5653 1.0000 1.000 0.4887 0.00719 0.00178 -0.0442 0.5334 1.0000 1.500 0.5438 0.00750 0.00196 -0.0440 0.5021 1.0000 2.000 0.5990 0.00779 0.00217 -0.0439 0.4661 1.0000 2.500 0.6538 0.00812 0.00239 -0.0438 0.4196 1.0000 3.000 0.7076 0.00862 0.00268 -0.0436 0.3668 1.0000 3.500 0.7612 0.00919 0.00309 -0.0435 0.3155 1.0000 4.000 0.8143 0.00983 0.00356 -0.0433 0.2634 1.0000 4.500 0.8667 0.01058 0.00414 -0.0431 0.2068 1.0000 5.000 0.9175 0.01159 0.00489 -0.0428 0.1413 1.0000 5.500 0.9664 0.01291 0.00591 -0.0422 0.0809 1.0000 6.000 1.0144 0.01434 0.00723 -0.0414 0.0524 1.0000 6.500 1.0625 0.01563 0.00861 -0.0405 0.0404 1.0000 7.000 1.1080 0.01718 0.01029 -0.0393 0.0331 1.0000 7.500 1.1489 0.01927 0.01250 -0.0375 0.0277 1.0000 8.000 1.1933 0.02072 0.01417 -0.0362 0.0242 1.0000 8.500 1.2271 0.02353 0.01716 -0.0337 0.0211 1.0000 9.000 1.2660 0.02536 0.01926 -0.0319 0.0187 1.0000 9.500 1.2965 0.02797 0.02205 -0.0294 0.0167 1.0000 10.000 1.3164 0.03186 0.02636 -0.0256 0.0153 1.0000 10.500 1.3325 0.03473 0.02956 -0.0216 0.0139 1.0000 11.000 1.3368 0.03816 0.03326 -0.0173 0.0130 1.0000 11.500 1.3307 0.04333 0.03872 -0.0147 0.0124 1.0000 12.500 1.2703 0.06421 0.06050 -0.0196 0.0118 1.0000 13.000 1.2393 0.07720 0.07387 -0.0270 0.0118 1.0000 13.500 1.1986 0.09281 0.08982 -0.0358 0.0118 1.0000 14.000 1.1605 0.10937 0.10665 -0.0453 0.0119 1.0000 14.500 1.1271 0.12705 0.12458 -0.0558 0.0122 1.0000 15.000 0.9577 0.19975 0.19743 -0.0892 0.0222 1.0000 15.500 0.9651 0.20892 0.20658 -0.0927 0.0213 1.0000 16.000 0.9734 0.22120 0.21884 -0.1012 0.0204 1.0000 16.500 0.9864 0.22979 0.22743 -0.1067 0.0178 1.0000 17.000 1.0027 0.23557 0.23323 -0.1098 0.0167 1.0000 17.500 1.0167 0.24313 0.24080 -0.1125 0.0160 1.0000 18.000 1.0301 0.25239 0.25004 -0.1190 0.0158 1.0000 18.500 1.0445 0.26195 0.25959 -0.1264 0.0139 1.0000 19.000 1.0603 0.26873 0.26638 -0.1309 0.0129 1.0000 19.500 1.0767 0.27383 0.27151 -0.1341 0.0122 1.0000