XFOIL Version 6.94 Calculated polar for: GOE 393 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 0.2146 0.01055 0.00289 -0.0320 0.5468 0.0943 0.500 0.2714 0.01062 0.00289 -0.0315 0.5283 0.1057 1.000 0.3274 0.01052 0.00276 -0.0311 0.5112 0.1140 1.500 0.3835 0.01037 0.00265 -0.0307 0.4919 0.1213 2.000 0.4393 0.01029 0.00258 -0.0302 0.4737 0.1329 2.500 0.4952 0.01020 0.00250 -0.0298 0.4488 0.1397 3.000 0.5510 0.01015 0.00246 -0.0294 0.4272 0.1501 3.500 0.6068 0.01015 0.00253 -0.0290 0.4043 0.1644 4.000 0.6670 0.00844 0.00273 -0.0299 0.3804 1.0000 4.500 0.7219 0.00876 0.00293 -0.0293 0.3598 1.0000 5.000 0.7767 0.00909 0.00322 -0.0287 0.3419 1.0000 5.500 0.8311 0.00947 0.00353 -0.0281 0.3169 1.0000 6.000 0.8854 0.00989 0.00390 -0.0276 0.2861 1.0000 6.500 0.9384 0.01055 0.00436 -0.0270 0.2226 1.0000 7.000 0.9862 0.01228 0.00554 -0.0263 0.1251 1.0000 7.500 1.0367 0.01336 0.00650 -0.0256 0.0985 1.0000 8.000 1.0869 0.01439 0.00748 -0.0249 0.0795 1.0000 8.500 1.1357 0.01559 0.00863 -0.0240 0.0570 1.0000 9.000 1.1828 0.01696 0.00996 -0.0230 0.0433 1.0000 9.500 1.2278 0.01854 0.01158 -0.0218 0.0381 1.0000 10.000 1.2707 0.02015 0.01329 -0.0204 0.0345 1.0000 10.500 1.3087 0.02223 0.01549 -0.0187 0.0322 1.0000 11.000 1.3432 0.02442 0.01777 -0.0169 0.0300 1.0000 11.500 1.3726 0.02691 0.02044 -0.0146 0.0285 1.0000 12.000 1.3953 0.02956 0.02324 -0.0120 0.0271 1.0000 12.500 1.4042 0.03331 0.02704 -0.0090 0.0259 1.0000 13.000 1.4171 0.03731 0.03138 -0.0090 0.0249 1.0000 13.500 1.4272 0.04217 0.03645 -0.0099 0.0238 1.0000 14.000 1.4347 0.04723 0.04160 -0.0104 0.0228 1.0000 14.500 1.4321 0.05389 0.04856 -0.0120 0.0219 1.0000 15.000 1.4262 0.06112 0.05609 -0.0143 0.0211 1.0000 15.500 1.4179 0.06879 0.06397 -0.0172 0.0203 1.0000 16.000 1.4128 0.07579 0.07105 -0.0193 0.0195 1.0000 16.500 1.3925 0.08591 0.08147 -0.0235 0.0189 1.0000 17.000 1.3683 0.09774 0.09364 -0.0295 0.0185 1.0000 17.500 1.3421 0.11044 0.10667 -0.0360 0.0181 1.0000 18.000 1.3152 0.12382 0.12032 -0.0431 0.0177 1.0000 18.500 1.2889 0.13784 0.13458 -0.0511 0.0172 1.0000