XFOIL Version 6.96 Calculated polar for: FX 38-153 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.000 -0.5763 0.05683 0.05432 -0.1183 0.9527 0.0034 -13.750 -0.6015 0.05001 0.04726 -0.1216 0.9501 0.0034 -13.500 -0.6198 0.04507 0.04211 -0.1228 0.9474 0.0034 -13.250 -0.6324 0.04126 0.03810 -0.1229 0.9449 0.0034 -13.000 -0.6409 0.03812 0.03477 -0.1223 0.9424 0.0034 -12.750 -0.6456 0.03546 0.03191 -0.1214 0.9398 0.0034 -12.500 -0.6468 0.03314 0.02942 -0.1204 0.9378 0.0034 -12.250 -0.6451 0.03109 0.02721 -0.1193 0.9358 0.0035 -12.000 -0.6406 0.02928 0.02524 -0.1182 0.9338 0.0035 -11.750 -0.6337 0.02766 0.02346 -0.1170 0.9318 0.0035 -11.500 -0.6245 0.02621 0.02186 -0.1158 0.9300 0.0036 -11.250 -0.6131 0.02489 0.02040 -0.1148 0.9282 0.0036 -11.000 -0.6001 0.02368 0.01904 -0.1138 0.9264 0.0037 -10.750 -0.5851 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8.500 1.1741 0.01893 0.01171 -0.0771 0.0104 0.7939 8.750 1.1932 0.01945 0.01227 -0.0761 0.0101 0.7948 9.000 1.2124 0.01995 0.01280 -0.0751 0.0100 0.7958 9.250 1.2319 0.02042 0.01330 -0.0742 0.0098 0.7968 9.500 1.2509 0.02093 0.01384 -0.0733 0.0096 0.7979 9.750 1.2696 0.02146 0.01441 -0.0723 0.0094 0.7988 10.000 1.2879 0.02201 0.01500 -0.0713 0.0091 0.7996 10.250 1.3053 0.02262 0.01564 -0.0701 0.0088 0.8003 10.500 1.3226 0.02322 0.01629 -0.0690 0.0086 0.8011 10.750 1.3394 0.02385 0.01697 -0.0678 0.0083 0.8020 11.000 1.3555 0.02453 0.01769 -0.0666 0.0080 0.8030 11.250 1.3704 0.02530 0.01850 -0.0652 0.0077 0.8039 11.500 1.3844 0.02612 0.01938 -0.0637 0.0074 0.8047 11.750 1.4015 0.02671 0.02002 -0.0627 0.0072 0.8056 12.000 1.4178 0.02736 0.02072 -0.0617 0.0069 0.8065 12.250 1.4338 0.02806 0.02146 -0.0606 0.0064 0.8075 12.500 1.4482 0.02886 0.02234 -0.0593 0.0051 0.8084 12.750 1.4607 0.02979 0.02319 -0.0580 0.0024 0.8095 13.000 1.4701 0.03098 0.02444 -0.0562 0.0021 0.8106 13.250 1.4793 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0.07654 -0.0406 0.0010 0.8290 18.250 1.4925 0.08625 0.08188 -0.0419 0.0010 0.8297 18.500 1.4793 0.09183 0.08760 -0.0437 0.0010 0.8303 18.750 1.4658 0.09761 0.09351 -0.0457 0.0010 0.8309 19.000 1.4488 0.10405 0.10009 -0.0482 0.0010 0.8315 19.250 1.4314 0.11072 0.10689 -0.0510 0.0010 0.8319