XFOIL Version 6.94 Calculated polar for: FX 75-141 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4755 0.01357 0.00816 -0.1173 0.7631 0.7240 0.500 0.5307 0.01356 0.00815 -0.1165 0.7555 0.7393 1.000 0.5871 0.01362 0.00814 -0.1165 0.7474 0.7514 1.500 0.6348 0.01343 0.00806 -0.1147 0.7361 0.7619 2.000 0.6920 0.01325 0.00790 -0.1146 0.7277 0.7742 2.500 0.7478 0.01301 0.00765 -0.1144 0.7183 0.7832 3.000 0.7987 0.01239 0.00710 -0.1128 0.7014 0.7932 3.500 0.8568 0.01210 0.00676 -0.1129 0.6897 0.8032 4.000 0.9035 0.01177 0.00656 -0.1108 0.6719 0.8120 4.500 0.9545 0.01149 0.00634 -0.1095 0.6512 0.8204 5.000 1.0049 0.01139 0.00617 -0.1082 0.6253 0.8287 6.000 1.0921 0.01173 0.00643 -0.1030 0.5637 0.8471 6.500 1.1316 0.01210 0.00685 -0.0999 0.5312 0.8574 7.000 1.1637 0.01259 0.00730 -0.0954 0.4860 0.8677 7.500 1.1830 0.01336 0.00791 -0.0888 0.4296 0.8827 8.000 1.1939 0.01477 0.00904 -0.0814 0.3490 0.9018 9.000 1.2148 0.01987 0.01339 -0.0719 0.1984 1.0000 9.500 1.2283 0.02267 0.01590 -0.0683 0.1474 1.0000 10.000 1.2395 0.02574 0.01874 -0.0648 0.1024 1.0000 10.500 1.2514 0.02889 0.02176 -0.0612 0.0765 1.0000 11.000 1.2659 0.03192 0.02480 -0.0583 0.0649 1.0000 11.500 1.2759 0.03536 0.02825 -0.0552 0.0528 1.0000 12.000 1.2922 0.03838 0.03142 -0.0528 0.0490 1.0000 12.500 1.3009 0.04229 0.03543 -0.0501 0.0427 1.0000 13.000 1.3011 0.04710 0.04039 -0.0471 0.0373 1.0000 13.500 1.3194 0.05041 0.04389 -0.0460 0.0340 1.0000 14.000 1.3281 0.05481 0.04847 -0.0440 0.0317 1.0000 14.500 1.3371 0.05935 0.05320 -0.0426 0.0306 1.0000 16.000 1.3435 0.07644 0.07098 -0.0406 0.0234 1.0000 16.500 1.3414 0.08299 0.07780 -0.0412 0.0219 1.0000 17.000 1.3348 0.09052 0.08558 -0.0428 0.0203 1.0000 17.500 1.3212 0.09934 0.09458 -0.0456 0.0184 1.0000 18.000 1.3104 0.10813 0.10376 -0.0483 0.0190 1.0000 18.500 1.2828 0.12006 0.11605 -0.0536 0.0185 1.0000 19.000 1.2493 0.13427 0.13075 -0.0612 0.0192 1.0000 19.500 1.2110 0.15039 0.14723 -0.0716 0.0192 1.0000