XFOIL Version 6.96 Calculated polar for: FX 71-L-150/20 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.000 -0.9408 0.11713 0.11233 0.0037 1.0000 0.0177 -16.750 -0.9633 0.10790 0.10289 -0.0021 1.0000 0.0177 -16.500 -0.9783 0.10070 0.09552 -0.0064 1.0000 0.0176 -16.250 -0.9944 0.09363 0.08825 -0.0106 1.0000 0.0176 -16.000 -1.0059 0.08768 0.08212 -0.0138 1.0000 0.0176 -15.750 -1.0162 0.08222 0.07648 -0.0166 1.0000 0.0176 -15.500 -1.0257 0.07710 0.07117 -0.0190 1.0000 0.0176 -15.250 -1.0307 0.07288 0.06679 -0.0208 1.0000 0.0176 -15.000 -1.0345 0.06897 0.06272 -0.0223 1.0000 0.0176 -14.750 -1.0370 0.06534 0.05894 -0.0234 1.0000 0.0176 -14.500 -1.0377 0.06209 0.05554 -0.0243 1.0000 0.0176 -14.250 -1.0373 0.05909 0.05239 -0.0249 1.0000 0.0177 -14.000 -1.0340 0.05650 0.04970 -0.0252 1.0000 0.0177 -13.750 -1.0305 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0.6553 1.000 0.1140 0.01269 0.00537 0.0000 0.6278 0.6590 1.250 0.1426 0.01270 0.00537 0.0000 0.6237 0.6630 1.500 0.1712 0.01271 0.00541 -0.0002 0.6178 0.6672 1.750 0.1994 0.01270 0.00546 -0.0001 0.6122 0.6702 2.000 0.2276 0.01269 0.00547 0.0001 0.6069 0.6740 2.250 0.2558 0.01269 0.00553 0.0002 0.5997 0.6782 2.500 0.2840 0.01265 0.00553 0.0003 0.5906 0.6824 2.750 0.3123 0.01261 0.00547 0.0004 0.5823 0.6865 3.000 0.3404 0.01257 0.00551 0.0005 0.5715 0.6895 3.250 0.3682 0.01250 0.00548 0.0008 0.5580 0.6925 3.500 0.3955 0.01244 0.00541 0.0012 0.5387 0.6960 3.750 0.4224 0.01241 0.00532 0.0016 0.5098 0.6999 4.000 0.4490 0.01247 0.00527 0.0019 0.4751 0.7038 4.250 0.4753 0.01262 0.00531 0.0022 0.4392 0.7075 4.500 0.4994 0.01295 0.00543 0.0028 0.3862 0.7104 4.750 0.5208 0.01359 0.00573 0.0036 0.3109 0.7135 5.000 0.5421 0.01430 0.00616 0.0043 0.2483 0.7172 5.250 0.5637 0.01501 0.00664 0.0048 0.1955 0.7213 5.500 0.5856 0.01567 0.00709 0.0053 0.1544 0.7258 5.750 0.6074 0.01629 0.00756 0.0059 0.1236 0.7298 6.000 0.6289 0.01688 0.00806 0.0065 0.0945 0.7333 6.250 0.6505 0.01746 0.00856 0.0072 0.0740 0.7372 6.500 0.6711 0.01811 0.00910 0.0079 0.0550 0.7412 6.750 0.6924 0.01868 0.00964 0.0085 0.0423 0.7455 7.000 0.7124 0.01931 0.01021 0.0093 0.0336 0.7495 7.250 0.7319 0.01991 0.01084 0.0103 0.0299 0.7536 7.500 0.7508 0.02054 0.01152 0.0113 0.0271 0.7582 7.750 0.7699 0.02115 0.01219 0.0122 0.0251 0.7632 8.000 0.7883 0.02179 0.01288 0.0131 0.0240 0.7681 8.250 0.8049 0.02244 0.01361 0.0143 0.0230 0.7723 8.500 0.8204 0.02312 0.01439 0.0156 0.0221 0.7773 8.750 0.8337 0.02384 0.01517 0.0171 0.0216 0.7830 9.000 0.8438 0.02459 0.01600 0.0190 0.0210 0.7885 9.250 0.8530 0.02549 0.01698 0.0207 0.0207 0.7945 9.500 0.8624 0.02653 0.01807 0.0220 0.0203 0.8016 9.750 0.8731 0.02758 0.01923 0.0231 0.0201 0.8086 10.000 0.8841 0.02874 0.02050 0.0239 0.0197 0.8164 10.250 0.8956 0.02991 0.02176 0.0246 0.0196 0.8252 10.500 0.9070 0.03115 0.02313 0.0252 0.0193 0.8360 10.750 0.9192 0.03242 0.02454 0.0256 0.0191 0.8508 11.000 0.9362 0.03376 0.02610 0.0249 0.0189 0.8809 11.250 0.9541 0.03532 0.02779 0.0235 0.0186 1.0000 11.500 0.9640 0.03684 0.02935 0.0239 0.0185 1.0000 11.750 0.9734 0.03844 0.03100 0.0242 0.0184 1.0000 12.000 0.9824 0.04009 0.03271 0.0246 0.0183 1.0000 12.250 0.9907 0.04183 0.03449 0.0249 0.0181 1.0000 12.500 0.9991 0.04360 0.03632 0.0251 0.0181 1.0000 12.750 1.0068 0.04547 0.03824 0.0253 0.0180 1.0000 13.000 1.0140 0.04742 0.04026 0.0254 0.0179 1.0000 13.250 1.0207 0.04946 0.04237 0.0255 0.0178 1.0000 13.500 1.0267 0.05161 0.04460 0.0255 0.0178 1.0000 13.750 1.0318 0.05391 0.04697 0.0254 0.0177 1.0000 14.000 1.0356 0.05640 0.04958 0.0251 0.0177 1.0000 14.250 1.0376 0.05919 0.05251 0.0247 0.0176 1.0000 14.500 1.0391 0.06204 0.05548 0.0242 0.0176 1.0000 14.750 1.0389 0.06519 0.05878 0.0233 0.0176 1.0000 15.000 1.0359 0.06890 0.06264 0.0222 0.0176 1.0000 15.250 1.0328 0.07270 0.06660 0.0208 0.0176 1.0000 15.500 1.0253 0.07734 0.07143 0.0188 0.0176 1.0000 15.750 1.0178 0.08214 0.07639 0.0165 0.0176 1.0000 16.000 1.0077 0.08756 0.08200 0.0138 0.0176 1.0000 16.250 0.9945 0.09381 0.08844 0.0103 0.0176 1.0000 16.500 0.9805 0.10049 0.09530 0.0064 0.0176 1.0000 16.750 0.9635 0.10811 0.10311 0.0018 0.0177 1.0000 17.000 0.9370 0.11831 0.11355 -0.0047 0.0177 1.0000