XFOIL Version 6.96 Calculated polar for: FX 61-140 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.3294 0.08495 0.08295 -0.0420 1.0000 0.0171 -10.000 -0.3381 0.07927 0.07730 -0.0436 1.0000 0.0175 -9.750 -0.3503 0.07264 0.07070 -0.0458 1.0000 0.0175 -9.500 -0.3758 0.06201 0.06007 -0.0514 1.0000 0.0169 -9.250 -0.4088 0.05375 0.05174 -0.0552 1.0000 0.0166 -9.000 -0.4445 0.04778 0.04568 -0.0562 1.0000 0.0161 -8.750 -0.4757 0.04435 0.04220 -0.0544 1.0000 0.0160 -8.500 -0.4899 0.03979 0.03749 -0.0578 0.9959 0.0160 -8.250 -0.4844 0.03457 0.03205 -0.0642 0.9891 0.0163 -8.000 -0.4684 0.02983 0.02708 -0.0690 0.9850 0.0172 -7.750 -0.4545 0.02584 0.02282 -0.0713 0.9775 0.0183 -7.500 -0.4192 0.02532 0.02190 -0.0741 0.9736 0.0207 -7.250 -0.4140 0.01740 0.01340 -0.0765 0.9647 0.0216 -7.000 -0.4294 0.02437 0.01964 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2.750 0.7960 0.01053 0.00436 -0.1116 0.4844 0.7279 3.000 0.8238 0.01061 0.00448 -0.1117 0.4782 0.7303 3.250 0.8516 0.01076 0.00460 -0.1118 0.4723 0.7330 3.500 0.8803 0.01084 0.00473 -0.1121 0.4659 0.7358 3.750 0.9089 0.01097 0.00484 -0.1124 0.4596 0.7385 4.000 0.9360 0.01106 0.00498 -0.1123 0.4534 0.7404 4.250 0.9632 0.01116 0.00512 -0.1123 0.4465 0.7424 4.500 0.9904 0.01132 0.00531 -0.1123 0.4403 0.7447 4.750 1.0181 0.01142 0.00547 -0.1123 0.4335 0.7472 5.000 1.0458 0.01160 0.00563 -0.1125 0.4270 0.7497 5.250 1.0741 0.01170 0.00578 -0.1127 0.4186 0.7522 5.500 1.1004 0.01180 0.00594 -0.1126 0.4087 0.7542 5.750 1.1262 0.01191 0.00607 -0.1123 0.3945 0.7561 6.000 1.1522 0.01206 0.00624 -0.1120 0.3804 0.7581 6.250 1.1782 0.01224 0.00643 -0.1119 0.3662 0.7604 6.500 1.2041 0.01246 0.00664 -0.1117 0.3486 0.7630 6.750 1.2293 0.01278 0.00690 -0.1115 0.3259 0.7654 7.000 1.2533 0.01316 0.00720 -0.1110 0.2996 0.7674 7.250 1.2759 0.01361 0.00758 -0.1103 0.2708 0.7693 7.500 1.2964 0.01427 0.00808 -0.1094 0.2320 0.7714 7.750 1.3119 0.01542 0.00889 -0.1078 0.1705 0.7736 8.000 1.3240 0.01688 0.00995 -0.1058 0.1087 0.7759 8.250 1.3375 0.01815 0.01097 -0.1039 0.0667 0.7784 8.500 1.3519 0.01931 0.01196 -0.1022 0.0393 0.7807 8.750 1.3662 0.02027 0.01287 -0.1003 0.0243 0.7826 9.000 1.3765 0.02147 0.01403 -0.0978 0.0124 0.7845 9.250 1.3885 0.02242 0.01503 -0.0955 0.0091 0.7868 9.500 1.3968 0.02339 0.01611 -0.0926 0.0078 0.7893 9.750 1.4070 0.02431 0.01712 -0.0901 0.0071 0.7919 10.000 1.4158 0.02535 0.01825 -0.0876 0.0066 0.7942 10.250 1.4213 0.02656 0.01957 -0.0849 0.0061 0.7963 10.500 1.4223 0.02811 0.02125 -0.0819 0.0058 0.7984 10.750 1.4177 0.03020 0.02348 -0.0787 0.0055 0.8009 11.000 1.4125 0.03257 0.02601 -0.0761 0.0054 0.8036 11.250 1.4126 0.03478 0.02837 -0.0745 0.0053 0.8062 11.500 1.4114 0.03736 0.03108 -0.0734 0.0052 0.8086 11.750 1.4094 0.04019 0.03405 -0.0726 0.0051 0.8107 12.000 1.4062 0.04335 0.03735 -0.0721 0.0050 0.8128 12.250 1.4026 0.04677 0.04092 -0.0719 0.0050 0.8152 12.500 1.3990 0.05037 0.04466 -0.0720 0.0049 0.8177 12.750 1.3948 0.05419 0.04861 -0.0724 0.0049 0.8201 13.000 1.3911 0.05809 0.05263 -0.0728 0.0048 0.8223 13.250 1.3871 0.06205 0.05673 -0.0734 0.0048 0.8243 13.500 1.3832 0.06609 0.06092 -0.0740 0.0048 0.8261 13.750 1.3802 0.07012 0.06509 -0.0747 0.0048 0.8281 14.000 1.3768 0.07431 0.06941 -0.0755 0.0047 0.8301 14.250 1.3742 0.07853 0.07378 -0.0764 0.0047 0.8322 14.500 1.3718 0.08281 0.07821 -0.0774 0.0047 0.8343 14.750 1.3684 0.08736 0.08291 -0.0785 0.0047 0.8363 15.000 1.3655 0.09193 0.08764 -0.0799 0.0048 0.8383 15.250 1.3610 0.09685 0.09274 -0.0814 0.0048 0.8403 15.500 1.3555 0.10208 0.09815 -0.0831 0.0048 0.8423 15.750 1.3492 0.10758 0.10384 -0.0853 0.0048 0.8444 16.000 1.3423 0.11338 0.10984 -0.0879 0.0049 0.8467 16.250 1.3311 0.12014 0.11681 -0.0911 0.0049 0.8484 16.500 1.3210 0.12686 0.12371 -0.0946 0.0050 0.8505 16.750 1.3103 0.13386 0.13090 -0.0985 0.0050 0.8524 17.000 1.2983 0.14131 0.13854 -0.1029 0.0051 0.8545 17.250 1.2865 0.14894 0.14635 -0.1077 0.0051 0.8568 17.500 1.2723 0.15739 0.15499 -0.1132 0.0052 0.8591 17.750 1.2570 0.16647 0.16423 -0.1193 0.0053 0.8615