XFOIL Version 6.94 Calculated polar for: MH 200 12.97% 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 0.3247 0.00904 0.00443 -0.0740 0.7728 0.7888 0.500 0.3798 0.00890 0.00428 -0.0739 0.7640 0.7995 1.000 0.4343 0.00882 0.00420 -0.0734 0.7533 0.8091 1.500 0.4906 0.00890 0.00421 -0.0733 0.7380 0.8166 2.000 0.5451 0.00889 0.00427 -0.0731 0.7292 0.8251 2.500 0.6003 0.00882 0.00424 -0.0729 0.7159 0.8319 3.000 0.6569 0.00876 0.00415 -0.0730 0.6990 0.8361 3.500 0.7104 0.00859 0.00407 -0.0726 0.6810 0.8459 4.000 0.7630 0.00852 0.00400 -0.0718 0.6514 0.8522 4.500 0.8138 0.00859 0.00406 -0.0708 0.6095 0.8589 5.000 0.8575 0.00906 0.00425 -0.0685 0.5311 0.8660 5.500 0.8958 0.00993 0.00475 -0.0655 0.4420 0.8733 6.000 0.9315 0.01091 0.00536 -0.0623 0.3545 0.8820 6.500 0.9647 0.01193 0.00606 -0.0587 0.2774 0.8920 7.000 1.0001 0.01289 0.00689 -0.0556 0.2203 0.9022 8.000 1.0612 0.01472 0.00850 -0.0476 0.1366 0.9327 8.500 1.0917 0.01579 0.00949 -0.0440 0.1013 0.9809 9.000 1.1253 0.01756 0.01102 -0.0422 0.0630 1.0000 9.500 1.1517 0.01964 0.01304 -0.0391 0.0418 1.0000 10.000 1.1849 0.02113 0.01466 -0.0370 0.0346 1.0000 11.000 1.2196 0.02648 0.02032 -0.0296 0.0223 1.0000 11.500 1.2450 0.02862 0.02273 -0.0274 0.0194 1.0000 12.000 1.2668 0.03113 0.02535 -0.0253 0.0158 1.0000 12.500 1.2557 0.03675 0.03130 -0.0208 0.0120 1.0000 13.000 1.2634 0.04089 0.03570 -0.0187 0.0107 1.0000 13.500 1.2812 0.04416 0.03915 -0.0176 0.0093 1.0000 14.000 1.2808 0.04968 0.04497 -0.0163 0.0081 1.0000 14.500 1.2755 0.05608 0.05167 -0.0159 0.0069 1.0000 15.000 1.2650 0.06348 0.05938 -0.0167 0.0063 1.0000 15.500 1.2450 0.07318 0.06944 -0.0190 0.0060 1.0000 16.000 1.2242 0.08413 0.08073 -0.0233 0.0057 1.0000 16.500 1.1964 0.09726 0.09421 -0.0298 0.0056 1.0000 17.000 1.1527 0.11443 0.11181 -0.0395 0.0059 1.0000 17.500 1.1153 0.13167 0.12936 -0.0505 0.0058 1.0000 18.000 1.0420 0.15879 0.15688 -0.0679 0.0067 1.0000 18.500 0.9343 0.20879 0.20688 -0.0905 0.0082 1.0000 19.000 0.9259 0.22789 0.22587 -0.0978 0.0081 1.0000 19.500 0.9261 0.24374 0.24169 -0.1036 0.0083 1.0000 20.000 0.9295 0.25802 0.25595 -0.1087 0.0090 1.0000 20.500 0.9266 0.27564 0.27357 -0.1130 0.0111 1.0000 21.000 0.9330 0.28841 0.28635 -0.1172 0.0111 1.0000 21.500 0.9387 0.30097 0.29898 -0.1212 0.0111 1.0000 22.000 0.9427 0.31351 0.31153 -0.1251 0.0110 1.0000 22.500 0.9441 0.32576 0.32381 -0.1286 0.0110 1.0000 23.000 0.9390 0.33741 0.33549 -0.1314 0.0109 1.0000