XFOIL Version 6.94 Calculated polar for: HQ 1.5/9 B AIRFOIL 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 0.2027 0.00765 0.00286 -0.0448 0.8424 0.8530 0.500 0.2521 0.00754 0.00278 -0.0427 0.8217 0.8832 1.000 0.3029 0.00742 0.00270 -0.0410 0.7991 0.9167 1.500 0.3675 0.00735 0.00264 -0.0424 0.7786 0.9556 2.000 0.4487 0.00733 0.00261 -0.0479 0.7556 0.9924 2.500 0.5019 0.00742 0.00273 -0.0477 0.7272 1.0000 3.000 0.5506 0.00757 0.00270 -0.0459 0.6722 1.0000 3.500 0.5896 0.00850 0.00267 -0.0424 0.4677 1.0000 4.000 0.6283 0.01027 0.00331 -0.0402 0.2522 1.0000 4.500 0.6760 0.01128 0.00394 -0.0392 0.1620 1.0000 5.000 0.7200 0.01279 0.00485 -0.0378 0.0521 1.0000 5.500 0.7671 0.01393 0.00581 -0.0367 0.0223 1.0000 6.000 0.8168 0.01469 0.00669 -0.0357 0.0189 1.0000 6.500 0.8662 0.01546 0.00759 -0.0348 0.0130 1.0000 7.000 0.9122 0.01664 0.00881 -0.0333 0.0046 1.0000 7.500 0.9564 0.01806 0.01047 -0.0314 0.0043 1.0000 8.000 0.9968 0.01991 0.01264 -0.0290 0.0043 1.0000 8.500 1.0308 0.02238 0.01547 -0.0258 0.0044 1.0000 9.000 1.0571 0.02583 0.01932 -0.0218 0.0046 1.0000 9.500 1.0755 0.03064 0.02465 -0.0172 0.0048 1.0000 10.000 1.0760 0.03794 0.03294 -0.0106 0.0053 1.0000 10.500 1.0326 0.04689 0.04274 -0.0020 0.0058 1.0000 11.000 0.9949 0.05498 0.05131 0.0007 0.0060 1.0000 11.500 0.9578 0.06492 0.06163 -0.0021 0.0060 1.0000 12.000 0.9193 0.07879 0.07581 -0.0110 0.0060 1.0000 12.500 0.8815 0.09891 0.09617 -0.0252 0.0059 1.0000 13.000 0.8342 0.12555 0.12282 -0.0387 0.0059 1.0000 13.500 0.8166 0.14220 0.13940 -0.0467 0.0063 1.0000 14.000 0.8153 0.15347 0.15063 -0.0523 0.0067 1.0000 14.500 0.8124 0.16780 0.16490 -0.0581 0.0090 1.0000 15.000 0.8114 0.18432 0.18138 -0.0651 0.0158 1.0000 15.500 0.8218 0.19339 0.19043 -0.0696 0.0157 1.0000 16.000 0.8344 0.20159 0.19861 -0.0738 0.0153 1.0000 16.500 0.8492 0.20904 0.20606 -0.0773 0.0149 1.0000 17.000 0.8676 0.21649 0.21351 -0.0796 0.0146 1.0000 17.500 0.8750 0.22549 0.22247 -0.0861 0.0144 1.0000 18.000 0.8881 0.23373 0.23069 -0.0911 0.0136 1.0000 18.500 0.9031 0.24104 0.23799 -0.0953 0.0128 1.0000 19.000 0.9187 0.24775 0.24471 -0.0991 0.0122 1.0000 19.500 0.9382 0.25460 0.25158 -0.1012 0.0118 1.0000 20.000 0.9491 0.26183 0.25877 -0.1070 0.0116 1.0000 20.500 0.9639 0.26909 0.26602 -0.1119 0.0109 1.0000 21.000 0.9794 0.27571 0.27264 -0.1161 0.0101 1.0000 21.500 0.9946 0.28189 0.27882 -0.1201 0.0096 1.0000 22.000 1.0105 0.28790 0.28485 -0.1234 0.0092 1.0000 22.500 1.0248 0.29457 0.29151 -0.1278 0.0090 1.0000 23.000 1.0396 0.30115 0.29808 -0.1328 0.0087 1.0000 23.500 1.0546 0.30738 0.30432 -0.1371 0.0081 1.0000 24.000 1.0691 0.31328 0.31023 -0.1413 0.0076 1.0000 24.500 1.0833 0.31891 0.31587 -0.1455 0.0072 1.0000 25.000 1.0971 0.32435 0.32133 -0.1494 0.0069 1.0000 25.500 1.1110 0.33056 0.32754 -0.1532 0.0067 1.0000 26.000 1.1242 0.33598 0.33297 -0.1581 0.0067 1.0000 26.500 1.1381 0.34172 0.33872 -0.1627 0.0065 1.0000 27.000 1.1516 0.34731 0.34432 -0.1671 0.0063 1.0000 27.500 1.1644 0.35266 0.34969 -0.1714 0.0059 1.0000 28.000 1.1769 0.35784 0.35488 -0.1758 0.0057 1.0000 28.500 1.1890 0.36291 0.35997 -0.1802 0.0054 1.0000 29.000 1.2007 0.36781 0.36489 -0.1846 0.0052 1.0000 29.500 1.2119 0.37253 0.36963 -0.1890 0.0051 1.0000 30.000 1.2227 0.37712 0.37425 -0.1934 0.0050 1.0000 30.500 1.2326 0.38168 0.37883 -0.1976 0.0048 1.0000 32.500 1.2712 0.39971 0.39695 -0.2155 0.0047 1.0000 33.000 1.2801 0.40390 0.40116 -0.2201 0.0047 1.0000 33.500 1.2888 0.40805 0.40533 -0.2247 0.0047 1.0000 34.000 1.2969 0.41203 0.40934 -0.2293 0.0047 1.0000 34.500 1.3045 0.41591 0.41325 -0.2339 0.0047 1.0000 35.000 1.3119 0.41972 0.41708 -0.2385 0.0047 1.0000 35.500 1.3189 0.42356 0.42095 -0.2430 0.0047 1.0000 36.000 1.3252 0.42702 0.42445 -0.2476 0.0047 1.0000 36.500 1.3313 0.43035 0.42781 -0.2522 0.0047 1.0000 37.000 1.3370 0.43355 0.43103 -0.2567 0.0046 1.0000 37.500 1.3425 0.43652 0.43404 -0.2614 0.0046 1.0000 38.000 1.3473 0.43934 0.43689 -0.2660 0.0046 1.0000 38.500 1.3520 0.44206 0.43964 -0.2705 0.0046 1.0000 39.000 1.3564 0.44477 0.44239 -0.2751 0.0044 1.0000 39.500 1.3601 0.44732 0.44496 -0.2796 0.0043 1.0000 40.000 1.3637 0.44980 0.44747 -0.2842 0.0041 1.0000 40.500 1.3666 0.45216 0.44986 -0.2888 0.0039 1.0000 41.000 1.3690 0.45445 0.45219 -0.2934 0.0037 1.0000 43.000 0.9407 0.69205 0.69113 -0.2609 0.0030 1.0000 43.500 0.9365 0.69972 0.69883 -0.2632 0.0030 1.0000 44.000 0.9319 0.70734 0.70648 -0.2653 0.0028 1.0000 44.500 0.9270 0.71455 0.71372 -0.2675 0.0027 1.0000 45.000 0.9217 0.72144 0.72063 -0.2697 0.0025 1.0000 45.500 0.9160 0.72775 0.72697 -0.2718 0.0024 1.0000 46.000 0.9102 0.73412 0.73337 -0.2739 0.0021 1.0000 46.500 0.9038 0.73962 0.73889 -0.2759 0.0021 1.0000 47.000 0.8972 0.74490 0.74420 -0.2779 0.0019 1.0000 47.500 0.8900 0.74967 0.74900 -0.2799 0.0019 1.0000