XFOIL Version 6.94 Calculated polar for: FX 61-140 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4805 0.00999 0.00401 -0.1080 0.5674 0.7001 0.500 0.5369 0.01021 0.00414 -0.1082 0.5510 0.7074 1.000 0.5945 0.01042 0.00422 -0.1088 0.5360 0.7138 1.500 0.6490 0.01055 0.00436 -0.1085 0.5219 0.7186 2.000 0.7047 0.01076 0.00455 -0.1086 0.5081 0.7240 2.500 0.7615 0.01103 0.00475 -0.1091 0.4944 0.7297 3.000 0.8188 0.01113 0.00493 -0.1096 0.4827 0.7350 3.500 0.8729 0.01140 0.00520 -0.1094 0.4703 0.7393 4.000 0.9279 0.01158 0.00548 -0.1094 0.4577 0.7444 4.500 0.9805 0.01177 0.00558 -0.1090 0.4271 0.7498 5.000 1.0361 0.01200 0.00585 -0.1093 0.4106 0.7545 5.500 1.0864 0.01224 0.00607 -0.1085 0.3721 0.7589 6.000 1.1361 0.01274 0.00648 -0.1076 0.3300 0.7631 6.500 1.1804 0.01380 0.00720 -0.1062 0.2547 0.7679 7.000 1.2093 0.01634 0.00890 -0.1027 0.1132 0.7728 7.500 1.2378 0.01857 0.01067 -0.0990 0.0322 0.7769 8.000 1.2664 0.02043 0.01245 -0.0950 0.0037 0.7816 8.500 1.3001 0.02174 0.01395 -0.0917 0.0028 0.7864 9.000 1.3246 0.02319 0.01560 -0.0871 0.0025 0.7910 9.500 1.3428 0.02504 0.01767 -0.0819 0.0023 0.7958 10.000 1.3520 0.02741 0.02032 -0.0762 0.0022 0.8007 10.500 1.3536 0.03066 0.02383 -0.0709 0.0022 0.8057 11.000 1.3496 0.03505 0.02848 -0.0671 0.0021 0.8107 11.500 1.3427 0.04064 0.03433 -0.0651 0.0021 0.8158 12.000 1.3342 0.04718 0.04116 -0.0644 0.0021 0.8209 12.500 1.3259 0.05453 0.04877 -0.0650 0.0021 0.8256 13.000 1.3187 0.06234 0.05682 -0.0663 0.0021 0.8301 13.500 1.3134 0.07046 0.06518 -0.0683 0.0022 0.8340 14.000 1.3093 0.07877 0.07377 -0.0706 0.0022 0.8383 14.500 1.3061 0.08742 0.08271 -0.0732 0.0022 0.8429 15.000 1.3023 0.09667 0.09229 -0.0765 0.0023 0.8479 15.500 1.2946 0.10721 0.10322 -0.0806 0.0024 0.8523 16.000 1.2806 0.11943 0.11588 -0.0862 0.0026 0.8562 16.500 1.2596 0.13358 0.13049 -0.0938 0.0027 0.8605 17.000 1.2358 0.14906 0.14639 -0.1032 0.0028 0.8654 17.500 1.2131 0.16515 0.16282 -0.1138 0.0029 0.8717 18.000 1.1878 0.18286 0.18087 -0.1257 0.0030 0.8791 18.500 1.1616 0.20258 0.20087 -0.1386 0.0031 0.8894 19.000 1.1261 0.22865 0.22710 -0.1534 0.0034 0.9014