XFOIL Version 6.94 Calculated polar for: FX 73-K-170/22 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 0.5186 0.01594 0.00995 -0.1228 0.7193 0.6934 0.500 0.5800 0.01574 0.00962 -0.1241 0.7162 0.7022 1.000 0.6178 0.01607 0.01001 -0.1212 0.7088 0.7085 1.500 0.6781 0.01585 0.00971 -0.1224 0.7052 0.7155 2.000 0.7190 0.01609 0.01001 -0.1201 0.6982 0.7210 2.500 0.7797 0.01581 0.00968 -0.1213 0.6938 0.7276 3.000 0.8223 0.01598 0.00993 -0.1192 0.6868 0.7334 4.000 0.9254 0.01584 0.00990 -0.1184 0.6744 0.7456 4.500 0.9921 0.01549 0.00953 -0.1208 0.6696 0.7524 5.000 1.0308 0.01573 0.00994 -0.1181 0.6612 0.7589 5.500 1.0865 0.01557 0.00984 -0.1183 0.6538 0.7662 6.000 1.1494 0.01525 0.00959 -0.1199 0.6459 0.7733 6.500 1.1943 0.01525 0.00976 -0.1182 0.6351 0.7815 7.000 1.2450 0.01507 0.00968 -0.1175 0.6225 0.7908 7.500 1.2917 0.01506 0.00982 -0.1162 0.6086 0.8018 8.000 1.3217 0.01526 0.01020 -0.1121 0.5885 0.8147 8.500 1.3592 0.01572 0.01084 -0.1100 0.5642 0.8311 9.000 1.3913 0.01682 0.01214 -0.1083 0.5302 0.8589 9.500 1.4412 0.01853 0.01405 -0.1113 0.4873 1.0000 10.000 1.4484 0.02146 0.01677 -0.1068 0.4352 1.0000 10.500 1.4411 0.02544 0.02046 -0.1011 0.3755 1.0000 11.000 1.4270 0.03017 0.02488 -0.0952 0.3144 1.0000 11.500 1.4153 0.03526 0.02972 -0.0902 0.2583 1.0000 12.000 1.3972 0.04135 0.03545 -0.0856 0.1924 1.0000 12.500 1.3800 0.04780 0.04151 -0.0816 0.1299 1.0000 13.000 1.3682 0.05409 0.04750 -0.0786 0.0820 1.0000 13.500 1.3635 0.05997 0.05323 -0.0763 0.0544 1.0000 14.000 1.3646 0.06559 0.05890 -0.0746 0.0429 1.0000 14.500 1.3644 0.07149 0.06490 -0.0733 0.0362 1.0000 15.000 1.3642 0.07760 0.07113 -0.0723 0.0291 1.0000 15.500 1.3578 0.08459 0.07824 -0.0715 0.0246 1.0000 16.000 1.3575 0.09103 0.08484 -0.0712 0.0216 1.0000 16.500 1.3537 0.09799 0.09194 -0.0711 0.0182 1.0000 17.000 1.3532 0.10444 0.09849 -0.0712 0.0170 1.0000 17.500 1.3562 0.11054 0.10481 -0.0715 0.0151 1.0000 18.000 1.3623 0.11614 0.11055 -0.0721 0.0143 1.0000 18.500 1.3731 0.12027 0.11468 -0.0716 0.0133 1.0000 19.000 1.3747 0.12705 0.12183 -0.0732 0.0125 1.0000 19.500 1.3784 0.13330 0.12837 -0.0749 0.0120 1.0000 20.000 1.3794 0.14003 0.13539 -0.0770 0.0117 1.0000 20.500 1.3801 0.14686 0.14226 -0.0803 0.0105 1.0000 21.000 1.3739 0.15567 0.15149 -0.0847 0.0109 1.0000 21.500 1.3569 0.16669 0.16286 -0.0912 0.0104 1.0000 22.000 1.3393 0.17878 0.17532 -0.0992 0.0104 1.0000 22.500 1.3252 0.19053 0.18738 -0.1075 0.0107 1.0000 23.000 1.2923 0.20845 0.20568 -0.1209 0.0106 1.0000