XFOIL Version 6.94 Calculated polar for: NACA CYH 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 0.3760 0.00797 0.00306 -0.0404 0.6225 0.9876 0.500 0.4765 0.00803 0.00298 -0.0499 0.5989 0.9995 1.000 0.5312 0.00806 0.00290 -0.0500 0.5741 1.0000 1.500 0.5831 0.00816 0.00288 -0.0495 0.5459 1.0000 2.000 0.6344 0.00834 0.00291 -0.0490 0.5103 1.0000 2.500 0.6845 0.00863 0.00302 -0.0483 0.4661 1.0000 3.000 0.7325 0.00906 0.00322 -0.0473 0.4181 1.0000 3.500 0.7794 0.00953 0.00350 -0.0461 0.3844 1.0000 4.000 0.8256 0.00997 0.00384 -0.0447 0.3604 1.0000 4.500 0.8717 0.01038 0.00421 -0.0433 0.3442 1.0000 5.000 0.9173 0.01079 0.00462 -0.0419 0.3291 1.0000 5.500 0.9626 0.01121 0.00505 -0.0404 0.3152 1.0000 6.000 1.0073 0.01167 0.00551 -0.0388 0.2983 1.0000 6.500 1.0524 0.01209 0.00595 -0.0373 0.2770 1.0000 7.000 1.0966 0.01259 0.00644 -0.0358 0.2503 1.0000 7.500 1.1368 0.01340 0.00708 -0.0339 0.2018 1.0000 8.000 1.1709 0.01475 0.00816 -0.0312 0.1511 1.0000 8.500 1.2061 0.01605 0.00933 -0.0288 0.1197 1.0000 9.000 1.2411 0.01730 0.01051 -0.0266 0.0977 1.0000 9.500 1.2738 0.01863 0.01180 -0.0242 0.0784 1.0000 10.000 1.2932 0.02048 0.01346 -0.0199 0.0449 1.0000 11.000 1.3099 0.02657 0.01958 -0.0123 0.0192 1.0000 11.500 1.3194 0.03026 0.02348 -0.0105 0.0177 1.0000 12.000 1.3251 0.03467 0.02810 -0.0095 0.0166 1.0000 12.500 1.3213 0.04035 0.03398 -0.0090 0.0159 1.0000 13.000 1.3041 0.04785 0.04168 -0.0092 0.0153 1.0000 13.500 1.2958 0.05476 0.04882 -0.0100 0.0148 1.0000 14.000 1.2869 0.06222 0.05649 -0.0114 0.0144 1.0000 14.500 1.2760 0.07032 0.06478 -0.0134 0.0139 1.0000 15.000 1.2651 0.07866 0.07330 -0.0156 0.0136 1.0000 15.500 1.2557 0.08692 0.08172 -0.0180 0.0132 1.0000 16.000 1.2489 0.09473 0.08965 -0.0202 0.0129 1.0000 16.500 1.2472 0.10116 0.09614 -0.0213 0.0125 1.0000 17.000 1.2453 0.10812 0.10327 -0.0231 0.0122 1.0000 17.500 1.2387 0.11686 0.11224 -0.0269 0.0119 1.0000 18.000 1.2319 0.12571 0.12134 -0.0310 0.0117 1.0000 18.500 1.2245 0.13484 0.13069 -0.0355 0.0114 1.0000 19.000 1.2158 0.14450 0.14058 -0.0407 0.0113 1.0000 19.500 1.2047 0.15503 0.15136 -0.0468 0.0112 1.0000 20.000 1.1895 0.16700 0.16359 -0.0541 0.0111 1.0000 20.500 1.1685 0.18128 0.17817 -0.0633 0.0112 1.0000 21.000 1.1353 0.20037 0.19760 -0.0755 0.0114 1.0000