XFOIL Version 6.96 Calculated polar for: AH 82-150 F 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.250 -0.3637 0.05093 0.04826 -0.1371 0.8034 0.0076 -12.000 -0.3978 0.04373 0.04090 -0.1408 0.8024 0.0076 -11.750 -0.4112 0.04058 0.03763 -0.1404 0.8014 0.0075 -11.500 -0.4160 0.03854 0.03551 -0.1392 0.8005 0.0074 -11.250 -0.4287 0.03608 0.03292 -0.1369 0.7995 0.0074 -11.000 -0.4475 0.03331 0.02996 -0.1333 0.7983 0.0074 -10.750 -0.4746 0.03006 0.02644 -0.1277 0.7971 0.0074 -10.500 -0.5016 0.02702 0.02308 -0.1209 0.7958 0.0075 -10.250 -0.5167 0.02404 0.01972 -0.1153 0.7948 0.0076 -10.000 -0.5150 0.02187 0.01725 -0.1120 0.7940 0.0077 -9.750 -0.5067 0.02010 0.01524 -0.1095 0.7932 0.0079 -9.500 -0.4920 0.01893 0.01389 -0.1079 0.7925 0.0081 -9.250 -0.4732 0.01827 0.01315 -0.1069 0.7917 0.0085 -9.000 -0.4533 0.01764 0.01242 -0.1060 0.7908 0.0087 -8.750 -0.4321 0.01724 0.01195 -0.1053 0.7898 0.0091 -8.500 -0.4104 0.01670 0.01134 -0.1047 0.7894 0.0095 -8.250 -0.3881 0.01617 0.01074 -0.1041 0.7889 0.0100 -8.000 -0.3657 0.01561 0.01008 -0.1035 0.7884 0.0105 -7.750 -0.3430 0.01506 0.00944 -0.1029 0.7879 0.0108 -7.500 -0.3191 0.01471 0.00903 -0.1025 0.7873 0.0110 -7.250 -0.3018 0.01347 0.00763 -0.1010 0.7867 0.0118 -7.000 -0.2799 0.01293 0.00705 -0.1003 0.7860 0.0127 -6.750 -0.2561 0.01261 0.00670 -0.0998 0.7854 0.0134 -6.500 -0.2315 0.01237 0.00644 -0.0996 0.7848 0.0145 -6.250 -0.2064 0.01216 0.00619 -0.0994 0.7841 0.0157 -6.000 -0.1841 0.01167 0.00566 -0.0986 0.7833 0.0183 -5.750 -0.1583 0.01153 0.00554 -0.0986 0.7826 0.0209 -5.500 -0.1318 0.01145 0.00545 -0.0986 0.7819 0.0227 -5.250 -0.1084 0.01107 0.00503 -0.0981 0.7813 0.0262 -5.000 -0.0826 0.01092 0.00488 -0.0980 0.7807 0.0292 -4.750 -0.0561 0.01082 0.00477 -0.0981 0.7801 0.0315 -4.500 -0.0301 0.01067 0.00459 -0.0980 0.7795 0.0335 -4.250 -0.0050 0.01045 0.00438 -0.0979 0.7789 0.0393 -4.000 0.0217 0.01036 0.00428 -0.0980 0.7782 0.0429 -3.750 0.0478 0.01023 0.00411 -0.0979 0.7775 0.0471 -3.500 0.0735 0.01012 0.00403 -0.0978 0.7768 0.0548 -3.250 0.0988 0.01006 0.00400 -0.0977 0.7759 0.0662 -3.000 0.1237 0.00982 0.00388 -0.0975 0.7753 0.0956 -2.750 0.1456 0.00937 0.00375 -0.0968 0.7746 0.1849 -2.500 0.1656 0.00880 0.00365 -0.0959 0.7736 0.3172 -2.250 0.1863 0.00827 0.00354 -0.0951 0.7722 0.4411 -2.000 0.2055 0.00759 0.00339 -0.0940 0.7706 0.5947 -1.750 0.2237 0.00705 0.00351 -0.0922 0.7691 0.7855 -1.500 0.2520 0.00716 0.00361 -0.0924 0.7678 0.8139 -1.250 0.2808 0.00724 0.00366 -0.0927 0.7665 0.8243 -1.000 0.3104 0.00730 0.00365 -0.0932 0.7652 0.8324 -0.750 0.3385 0.00753 0.00388 -0.0930 0.7636 0.8437 -0.500 0.3645 0.00791 0.00427 -0.0923 0.7617 0.8544 -0.250 0.3919 0.00798 0.00434 -0.0924 0.7600 0.8604 0.000 0.4189 0.00796 0.00432 -0.0923 0.7581 0.8627 0.250 0.4460 0.00799 0.00436 -0.0923 0.7563 0.8650 0.500 0.4736 0.00802 0.00439 -0.0924 0.7546 0.8675 0.750 0.5014 0.00813 0.00448 -0.0924 0.7531 0.8730 1.000 0.5268 0.00821 0.00457 -0.0917 0.7515 0.8784 1.250 0.5533 0.00831 0.00467 -0.0913 0.7501 0.8826 1.500 0.5826 0.00835 0.00469 -0.0919 0.7484 0.8844 1.750 0.6099 0.00829 0.00465 -0.0922 0.7466 0.8854 2.000 0.6377 0.00822 0.00460 -0.0926 0.7444 0.8861 2.250 0.6664 0.00815 0.00454 -0.0931 0.7421 0.8870 2.500 0.6959 0.00807 0.00447 -0.0939 0.7399 0.8875 2.750 0.7259 0.00799 0.00438 -0.0947 0.7379 0.8880 3.000 0.7562 0.00792 0.00430 -0.0956 0.7359 0.8883 3.250 0.7845 0.00788 0.00429 -0.0961 0.7333 0.8888 3.500 0.8105 0.00777 0.00423 -0.0960 0.7299 0.8895 3.750 0.8382 0.00766 0.00415 -0.0963 0.7266 0.8900 4.000 0.8668 0.00755 0.00405 -0.0968 0.7235 0.8904 4.250 0.8921 0.00740 0.00394 -0.0965 0.7160 0.8909 4.500 0.9187 0.00727 0.00384 -0.0966 0.7092 0.8913 4.750 0.9430 0.00718 0.00378 -0.0961 0.6972 0.8918 5.000 0.9653 0.00712 0.00370 -0.0952 0.6757 0.8924 5.250 0.9753 0.00732 0.00370 -0.0917 0.6295 0.8936 5.500 0.9731 0.00783 0.00397 -0.0859 0.5816 0.8952 5.750 0.9654 0.00829 0.00428 -0.0789 0.5451 0.8969 6.000 0.9572 0.00899 0.00482 -0.0723 0.5080 0.8987 6.250 0.9467 0.00993 0.00556 -0.0658 0.4664 0.9005 6.500 0.9378 0.01103 0.00645 -0.0599 0.4214 0.9020 6.750 0.9307 0.01219 0.00737 -0.0546 0.3735 0.9036 7.000 0.9260 0.01335 0.00827 -0.0499 0.3214 0.9051 7.250 0.9147 0.01489 0.00940 -0.0443 0.2462 0.9066 7.500 0.8922 0.01708 0.01095 -0.0374 0.1278 0.9084 7.750 0.8807 0.01899 0.01235 -0.0323 0.0300 0.9098 8.000 0.8916 0.01986 0.01315 -0.0304 0.0136 0.9106 8.250 0.9085 0.02042 0.01375 -0.0294 0.0119 0.9114 8.500 0.9250 0.02101 0.01439 -0.0283 0.0110 0.9121 8.750 0.9405 0.02167 0.01508 -0.0272 0.0102 0.9129 9.000 0.9537 0.02249 0.01595 -0.0257 0.0092 0.9137 9.250 0.9645 0.02348 0.01701 -0.0240 0.0082 0.9147 9.500 0.9780 0.02430 0.01789 -0.0227 0.0080 0.9155 9.750 0.9936 0.02502 0.01864 -0.0217 0.0075 0.9162 10.000 1.0057 0.02597 0.01965 -0.0203 0.0071 0.9170 10.250 1.0162 0.02703 0.02079 -0.0188 0.0069 0.9181 10.500 1.0288 0.02796 0.02177 -0.0176 0.0066 0.9192 10.750 1.0399 0.02900 0.02286 -0.0163 0.0062 0.9202 11.000 1.0476 0.03032 0.02423 -0.0146 0.0059 0.9214 11.250 1.0539 0.03179 0.02577 -0.0129 0.0058 0.9225 11.500 1.0461 0.03440 0.02850 -0.0098 0.0054 0.9236 11.750 1.0558 0.03575 0.02992 -0.0085 0.0052 0.9247 12.000 1.0652 0.03717 0.03141 -0.0073 0.0052 0.9258 12.250 1.0775 0.03838 0.03269 -0.0065 0.0050 0.9269 12.500 1.0893 0.03967 0.03405 -0.0056 0.0047 0.9280 12.750 1.0988 0.04123 0.03571 -0.0046 0.0046 0.9289 13.000 1.1097 0.04278 0.03734 -0.0037 0.0046 0.9297 13.250 1.1227 0.04435 0.03902 -0.0028 0.0045 0.9302 13.500 1.1365 0.04592 0.04070 -0.0021 0.0044 0.9311 13.750 1.1523 0.04762 0.04254 -0.0015 0.0045 0.9316 14.000 1.1712 0.05012 0.04526 -0.0011 0.0047 0.9312