XFOIL Version 6.96 Calculated polar for: HUGHES HELICOPTERS HH-02 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.5692 0.11466 0.11077 0.0264 1.0000 0.0912 -9.000 -0.5728 0.11062 0.10678 0.0193 1.0000 0.0955 -8.750 -0.5891 0.10595 0.10219 0.0047 1.0000 0.0967 -8.500 -0.5569 0.10119 0.09740 0.0149 1.0000 0.1005 -8.250 -0.5462 0.09747 0.09368 0.0128 1.0000 0.1059 -8.000 -0.5572 0.09193 0.08819 -0.0023 1.0000 0.1107 -7.750 -0.5392 0.08789 0.08418 0.0020 1.0000 0.1153 -7.500 -0.5305 0.08368 0.07997 -0.0040 1.0000 0.1234 -7.250 -0.5238 0.07775 0.07403 -0.0115 1.0000 0.1291 -6.750 -0.4989 0.06884 0.06503 -0.0198 1.0000 0.1455 -6.500 -0.4924 0.06381 0.05984 -0.0267 1.0000 0.1580 -6.250 -0.4766 0.06130 0.05738 -0.0252 1.0000 0.1656 -6.000 -0.4762 0.05804 0.05405 -0.0259 1.0000 0.1757 -5.750 -0.4591 0.05451 0.05043 -0.0282 0.9950 0.1912 -5.500 -0.4204 0.03744 0.03100 -0.0398 0.9862 0.0815 -5.250 -0.3866 0.03314 0.02629 -0.0422 0.9811 0.0798 -5.000 -0.3542 0.02957 0.02222 -0.0436 0.9751 0.0771 -4.750 -0.3174 0.02656 0.01862 -0.0453 0.9700 0.0755 -4.500 -0.2850 0.02481 0.01646 -0.0460 0.9639 0.0788 -4.250 -0.2513 0.02355 0.01473 -0.0467 0.9577 0.0823 -4.000 -0.2204 0.02170 0.01287 -0.0473 0.9520 0.0863 -3.750 -0.1917 0.02097 0.01204 -0.0474 0.9451 0.0951 -3.500 -0.1635 0.02003 0.01120 -0.0474 0.9389 0.1042 -3.250 -0.1390 0.01937 0.01061 -0.0468 0.9316 0.1189 -3.000 -0.1149 0.01886 0.01024 -0.0460 0.9250 0.1466 -2.750 -0.0999 0.01671 0.00999 -0.0443 0.9176 0.4905 -2.500 -0.0827 0.01702 0.01061 -0.0413 0.9101 0.6407 -2.250 -0.0622 0.01732 0.01092 -0.0392 0.9028 0.7017 -2.000 -0.0402 0.01726 0.01095 -0.0376 0.8950 0.7562 -1.750 0.0249 0.01687 0.01108 -0.0422 0.8909 0.8912 -1.500 0.0816 0.01714 0.01113 -0.0482 0.8844 0.9953 -1.250 0.1087 0.01747 0.01125 -0.0493 0.8757 1.0000 -1.000 0.1317 0.01787 0.01146 -0.0492 0.8670 1.0000 -0.750 0.1540 0.01831 0.01173 -0.0485 0.8586 1.0000 -0.500 0.1779 0.01865 0.01192 -0.0481 0.8491 1.0000 -0.250 0.2015 0.01896 0.01211 -0.0476 0.8387 1.0000 0.000 0.2234 0.01927 0.01230 -0.0462 0.8283 1.0000 0.250 0.2433 0.01954 0.01244 -0.0439 0.8188 1.0000 0.500 0.2676 0.01975 0.01257 -0.0433 0.8072 1.0000 0.750 0.2908 0.01998 0.01273 -0.0422 0.7968 1.0000 1.000 0.3102 0.02011 0.01278 -0.0395 0.7891 1.0000 1.250 0.3355 0.02030 0.01292 -0.0391 0.7775 1.0000 1.500 0.3593 0.02045 0.01304 -0.0381 0.7668 1.0000 1.750 0.3783 0.02035 0.01288 -0.0349 0.7597 1.0000 2.000 0.4033 0.02043 0.01296 -0.0342 0.7474 1.0000 2.250 0.4269 0.02043 0.01295 -0.0329 0.7360 1.0000 2.500 0.4452 0.02004 0.01251 -0.0291 0.7295 1.0000 2.750 0.4694 0.01993 0.01241 -0.0279 0.7166 1.0000 3.000 0.4926 0.01971 0.01223 -0.0261 0.7042 1.0000 3.250 0.5149 0.01937 0.01189 -0.0239 0.6924 1.0000 3.500 0.5354 0.01883 0.01133 -0.0208 0.6822 1.0000 3.750 0.5563 0.01826 0.01075 -0.0178 0.6708 1.0000 4.000 0.5789 0.01779 0.01032 -0.0155 0.6565 1.0000 4.250 0.6013 0.01730 0.00983 -0.0130 0.6413 1.0000 4.500 0.6248 0.01690 0.00944 -0.0110 0.6229 1.0000 4.750 0.6489 0.01656 0.00910 -0.0093 0.6010 1.0000 5.000 0.6724 0.01624 0.00876 -0.0073 0.5772 1.0000 5.250 0.6972 0.01607 0.00854 -0.0058 0.5480 1.0000 5.500 0.7232 0.01609 0.00849 -0.0049 0.5122 1.0000 5.750 0.7488 0.01626 0.00850 -0.0040 0.4756 1.0000 6.000 0.7757 0.01668 0.00878 -0.0039 0.4347 1.0000 6.250 0.8020 0.01727 0.00917 -0.0037 0.3976 1.0000 6.500 0.8282 0.01802 0.00974 -0.0037 0.3628 1.0000 6.750 0.8540 0.01886 0.01045 -0.0038 0.3313 1.0000 7.000 0.8796 0.01977 0.01124 -0.0039 0.3024 1.0000 7.250 0.9048 0.02069 0.01207 -0.0040 0.2756 1.0000 7.500 0.9295 0.02165 0.01289 -0.0040 0.2515 1.0000 7.750 0.9544 0.02263 0.01395 -0.0041 0.2276 1.0000 8.000 0.9781 0.02370 0.01489 -0.0040 0.2071 1.0000 8.250 1.0018 0.02481 0.01608 -0.0041 0.1858 1.0000 8.500 1.0245 0.02597 0.01723 -0.0040 0.1672 1.0000 8.750 1.0465 0.02725 0.01847 -0.0037 0.1508 1.0000 9.000 1.0682 0.02866 0.01990 -0.0034 0.1365 1.0000 9.250 1.0891 0.03011 0.02143 -0.0031 0.1232 1.0000 9.500 1.1093 0.03177 0.02324 -0.0026 0.1117 1.0000 9.750 1.1285 0.03355 0.02514 -0.0021 0.1013 1.0000 10.000 1.1475 0.03545 0.02700 -0.0016 0.0921 1.0000 10.250 1.1643 0.03714 0.02893 -0.0011 0.0835 1.0000 10.500 1.1787 0.03967 0.03172 -0.0005 0.0762 1.0000 10.750 1.1948 0.04165 0.03364 0.0001 0.0693 1.0000 11.000 1.2013 0.04472 0.03722 0.0009 0.0644 1.0000 11.250 1.2100 0.04693 0.03962 0.0015 0.0597 1.0000 11.500 1.2182 0.05090 0.04364 0.0022 0.0563 1.0000 11.750 1.2096 0.05431 0.04757 0.0028 0.0548 1.0000 12.000 1.1953 0.05783 0.05144 0.0039 0.0536 1.0000 12.250 1.1790 0.06180 0.05571 0.0043 0.0527 1.0000 12.500 1.1602 0.06637 0.06056 0.0039 0.0523 1.0000 12.750 1.1375 0.07182 0.06628 0.0024 0.0523 1.0000 13.000 1.1110 0.07837 0.07308 -0.0004 0.0530 1.0000 13.250 1.0829 0.08592 0.08083 -0.0043 0.0539 1.0000 13.500 1.0553 0.09429 0.08934 -0.0091 0.0550 1.0000 13.750 1.0294 0.10325 0.09840 -0.0143 0.0560 1.0000 14.000 0.8940 0.15009 0.14514 -0.0436 0.0799 1.0000 14.250 0.8945 0.15622 0.15127 -0.0453 0.0805 1.0000