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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.250 -1.0609 0.05927 0.05336 -0.0307 1.0000 0.0339 -13.000 -1.0637 0.05610 0.05003 -0.0304 1.0000 0.0338 -12.750 -1.0705 0.05319 0.04693 -0.0297 1.0000 0.0338 -12.500 -1.0694 0.05041 0.04399 -0.0290 1.0000 0.0337 -12.250 -1.0711 0.04783 0.04121 -0.0279 1.0000 0.0337 -12.000 -1.0639 0.04534 0.03858 -0.0270 1.0000 0.0335 -11.750 -1.0571 0.04304 0.03610 -0.0259 1.0000 0.0335 -11.500 -1.0454 0.04086 0.03375 -0.0250 1.0000 0.0333 -11.250 -1.0301 0.03876 0.03149 -0.0243 1.0000 0.0332 -11.000 -1.0113 0.03671 0.02928 -0.0239 1.0000 0.0331 -10.750 -0.9903 0.03491 0.02735 -0.0237 1.0000 0.0331 -10.500 -0.9665 0.03323 0.02554 -0.0237 1.0000 0.0332 -10.250 -0.9414 0.03172 0.02394 -0.0237 1.0000 0.0333 -10.000 -0.9160 0.03038 0.02253 -0.0237 1.0000 0.0335 -9.750 -0.8916 0.02917 0.02124 -0.0236 1.0000 0.0339 -9.500 -0.8652 0.02795 0.02015 -0.0237 1.0000 0.0344 -9.250 -0.8407 0.02683 0.01908 -0.0243 0.9403 0.0350 -9.000 -0.8059 0.02563 0.01778 -0.0268 0.9043 0.0360 -8.750 -0.7872 0.02466 0.01670 -0.0265 0.8857 0.0369 -8.500 -0.7732 0.02380 0.01573 -0.0252 0.8733 0.0377 -8.250 -0.7648 0.02295 0.01487 -0.0231 0.8629 0.0387 -8.000 -0.7529 0.02220 0.01407 -0.0214 0.8541 0.0403 -7.750 -0.7391 0.02146 0.01326 -0.0198 0.8459 0.0422 -7.500 -0.7251 0.02074 0.01250 -0.0183 0.8391 0.0451 -7.250 -0.7101 0.01990 0.01165 -0.0169 0.8327 0.0506 -7.000 -0.6974 0.01886 0.01070 -0.0152 0.8267 0.0640 -6.750 -0.6849 0.01777 0.00985 -0.0136 0.8215 0.0991 -6.500 -0.6700 0.01667 0.00911 -0.0125 0.8155 0.1539 -6.250 -0.6545 0.01569 0.00847 -0.0113 0.8098 0.2192 -6.000 -0.6389 0.01479 0.00793 -0.0100 0.8051 0.2934 -5.750 -0.6205 0.01401 0.00757 -0.0090 0.7998 0.3736 -5.500 -0.5983 0.01366 0.00746 -0.0082 0.7946 0.4340 -5.250 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-0.500 -0.0549 0.01695 0.01061 -0.0003 0.7108 0.6915 -0.250 -0.0277 0.01705 0.01070 0.0001 0.7071 0.6955 0.000 0.0000 0.01709 0.01080 0.0000 0.7007 0.7006 0.250 0.0277 0.01705 0.01070 -0.0001 0.6955 0.7071 0.500 0.0549 0.01695 0.01061 0.0003 0.6915 0.7108 0.750 0.0821 0.01696 0.01060 0.0008 0.6883 0.7140 1.000 0.1097 0.01704 0.01077 0.0006 0.6822 0.7179 1.250 0.1374 0.01698 0.01073 0.0006 0.6761 0.7224 1.500 0.1657 0.01686 0.01055 0.0006 0.6714 0.7273 1.750 0.1931 0.01674 0.01041 0.0010 0.6676 0.7306 2.000 0.2198 0.01676 0.01055 0.0012 0.6599 0.7341 2.250 0.2473 0.01660 0.01042 0.0016 0.6529 0.7383 2.500 0.2754 0.01638 0.01015 0.0021 0.6477 0.7431 2.750 0.3031 0.01633 0.01013 0.0020 0.6389 0.7484 3.000 0.3300 0.01604 0.00990 0.0028 0.6310 0.7521 3.250 0.3576 0.01574 0.00959 0.0035 0.6232 0.7562 3.500 0.3849 0.01534 0.00922 0.0041 0.6101 0.7607 3.750 0.4128 0.01488 0.00874 0.0046 0.5949 0.7652 4.000 0.4406 0.01446 0.00828 0.0051 0.5805 0.7691 4.250 0.4674 0.01417 0.00804 0.0057 0.5669 0.7729 4.500 0.4942 0.01394 0.00786 0.0062 0.5498 0.7774 4.750 0.5213 0.01376 0.00767 0.0066 0.5294 0.7822 5.000 0.5487 0.01368 0.00758 0.0068 0.5061 0.7867 5.250 0.5739 0.01358 0.00749 0.0075 0.4755 0.7903 5.500 0.5983 0.01366 0.00746 0.0082 0.4339 0.7946 5.750 0.6206 0.01401 0.00757 0.0090 0.3736 0.7998 6.000 0.6390 0.01478 0.00793 0.0100 0.2940 0.8051 6.250 0.6544 0.01570 0.00847 0.0113 0.2184 0.8098 6.500 0.6698 0.01669 0.00912 0.0125 0.1527 0.8155 6.750 0.6852 0.01775 0.00985 0.0136 0.1000 0.8214 7.000 0.6973 0.01887 0.01071 0.0152 0.0637 0.8267 7.250 0.7102 0.01990 0.01164 0.0169 0.0509 0.8327 7.500 0.7251 0.02075 0.01251 0.0183 0.0450 0.8391 7.750 0.7388 0.02149 0.01328 0.0198 0.0421 0.8459 8.000 0.7531 0.02220 0.01407 0.0213 0.0403 0.8541 8.250 0.7652 0.02295 0.01486 0.0230 0.0388 0.8628 8.500 0.7734 0.02381 0.01573 0.0252 0.0378 0.8733 8.750 0.7875 0.02467 0.01670 0.0264 0.0370 0.8856 9.000 0.8062 0.02563 0.01779 0.0268 0.0359 0.9043 9.250 0.8411 0.02683 0.01908 0.0242 0.0350 0.9400 9.500 0.8656 0.02796 0.02015 0.0237 0.0343 1.0000 9.750 0.8921 0.02917 0.02124 0.0236 0.0339 1.0000 10.000 0.9165 0.03040 0.02255 0.0237 0.0335 1.0000 10.250 0.9423 0.03172 0.02393 0.0236 0.0333 1.0000 10.500 0.9672 0.03324 0.02556 0.0236 0.0332 1.0000 10.750 0.9910 0.03490 0.02733 0.0236 0.0331 1.0000 11.000 1.0122 0.03671 0.02928 0.0238 0.0331 1.0000 11.250 1.0306 0.03874 0.03147 0.0243 0.0332 1.0000 11.500 1.0459 0.04085 0.03374 0.0249 0.0333 1.0000 11.750 1.0580 0.04308 0.03614 0.0258 0.0335 1.0000 12.000 1.0636 0.04534 0.03858 0.0270 0.0335 1.0000 12.250 1.0686 0.04788 0.04129 0.0280 0.0336 1.0000 12.500 1.0671 0.05039 0.04399 0.0291 0.0336 1.0000 12.750 1.0704 0.05318 0.04692 0.0297 0.0338 1.0000 13.000 1.0660 0.05611 0.05002 0.0303 0.0338 1.0000 13.250 1.0605 0.05926 0.05334 0.0307 0.0339 1.0000