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 = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.000 -0.6706 0.08363 0.08066 0.0279 0.8311 0.0165 -7.750 -0.6735 0.07366 0.07064 0.0167 0.8272 0.0161 -7.500 -0.6807 0.06014 0.05680 0.0059 0.8242 0.0154 -7.250 -0.6863 0.04745 0.04346 0.0013 0.8217 0.0151 -7.000 -0.6768 0.04132 0.03679 0.0006 0.8195 0.0153 -6.750 -0.6605 0.03699 0.03199 0.0004 0.8166 0.0156 -6.500 -0.6404 0.03323 0.02774 0.0003 0.8128 0.0161 -6.250 -0.6192 0.02998 0.02398 0.0006 0.8096 0.0167 -6.000 -0.5965 0.02746 0.02094 0.0013 0.8069 0.0180 -5.750 -0.5730 0.02532 0.01826 0.0022 0.8046 0.0192 -5.500 -0.5475 0.02378 0.01656 0.0023 0.8011 0.0200 -5.250 -0.5206 0.02256 0.01517 0.0023 0.7970 0.0209 -5.000 -0.4944 0.02139 0.01380 0.0027 0.7937 0.0219 -4.750 -0.4687 0.02035 0.01256 0.0034 0.7909 0.0234 -4.500 -0.4421 0.01959 0.01158 0.0039 0.7880 0.0251 -4.250 -0.4143 0.01846 0.01044 0.0037 0.7833 0.0268 -4.000 -0.3873 0.01771 0.00963 0.0040 0.7795 0.0285 -3.750 -0.3610 0.01702 0.00885 0.0045 0.7764 0.0306 -3.500 -0.3340 0.01652 0.00822 0.0049 0.7732 0.0332 -3.250 -0.3054 0.01575 0.00746 0.0046 0.7681 0.0365 -3.000 -0.2778 0.01524 0.00689 0.0048 0.7641 0.0400 -2.750 -0.2509 0.01477 0.00634 0.0052 0.7609 0.0450 -2.500 -0.2224 0.01434 0.00587 0.0051 0.7565 0.0522 -2.250 -0.1934 0.01392 0.00547 0.0049 0.7515 0.0634 -2.000 -0.1659 0.01345 0.00509 0.0051 0.7476 0.0923 -1.750 -0.1397 0.01278 0.00474 0.0054 0.7445 0.1795 -1.500 -0.1112 0.01196 0.00456 0.0047 0.7385 0.3335 -1.250 -0.0850 0.01138 0.00451 0.0050 0.7339 0.4812 -1.000 -0.0587 0.01115 0.00441 0.0056 0.7302 0.5462 -0.750 -0.0304 0.01098 0.00442 0.0057 0.7244 0.6131 -0.500 -0.0031 0.01083 0.00435 0.0061 0.7191 0.6576 -0.250 0.0237 0.01066 0.00417 0.0067 0.7148 0.6814 0.000 0.0522 0.01046 0.00404 0.0068 0.7058 0.7093 0.250 0.0780 0.01011 0.00378 0.0077 0.6972 0.7461 0.500 0.1043 0.00967 0.00358 0.0086 0.6875 0.7994 0.750 0.1529 0.00947 0.00356 0.0048 0.6785 0.9815 1.000 0.1870 0.00945 0.00344 0.0036 0.6710 1.0000 1.250 0.2159 0.00947 0.00340 0.0034 0.6617 1.0000 1.500 0.2437 0.00948 0.00331 0.0037 0.6534 1.0000 1.750 0.2722 0.00951 0.00327 0.0036 0.6434 1.0000 2.000 0.3007 0.00954 0.00325 0.0036 0.6331 1.0000 2.250 0.3288 0.00958 0.00323 0.0037 0.6222 1.0000 2.500 0.3570 0.00963 0.00320 0.0038 0.6101 1.0000 2.750 0.3855 0.00969 0.00321 0.0038 0.5960 1.0000 3.000 0.4141 0.00977 0.00323 0.0037 0.5803 1.0000 3.250 0.4429 0.00987 0.00328 0.0036 0.5626 1.0000 3.500 0.4717 0.00999 0.00334 0.0034 0.5426 1.0000 3.750 0.5005 0.01013 0.00341 0.0033 0.5207 1.0000 4.000 0.5297 0.01031 0.00353 0.0030 0.4944 1.0000 4.250 0.5590 0.01055 0.00365 0.0025 0.4630 1.0000 4.500 0.5886 0.01085 0.00382 0.0020 0.4267 1.0000 4.750 0.6184 0.01126 0.00404 0.0012 0.3874 1.0000 5.000 0.6481 0.01170 0.00435 0.0004 0.3529 1.0000 5.250 0.6777 0.01217 0.00469 -0.0004 0.3231 1.0000 5.500 0.7069 0.01262 0.00505 -0.0012 0.2980 1.0000 5.750 0.7358 0.01305 0.00544 -0.0018 0.2757 1.0000 6.000 0.7645 0.01351 0.00584 -0.0025 0.2538 1.0000 6.250 0.7929 0.01398 0.00626 -0.0031 0.2326 1.0000 6.500 0.8210 0.01447 0.00669 -0.0037 0.2110 1.0000 7.000 0.8763 0.01550 0.00767 -0.0048 0.1759 1.0000 7.250 0.9035 0.01603 0.00819 -0.0052 0.1602 1.0000 7.500 0.9302 0.01661 0.00876 -0.0057 0.1440 1.0000 7.750 0.9565 0.01722 0.00937 -0.0061 0.1286 1.0000 8.000 0.9824 0.01786 0.01001 -0.0065 0.1148 1.0000 8.250 1.0078 0.01854 0.01070 -0.0068 0.1025 1.0000 8.500 1.0325 0.01927 0.01143 -0.0071 0.0908 1.0000 8.750 1.0565 0.02007 0.01225 -0.0074 0.0803 1.0000 9.000 1.0802 0.02085 0.01308 -0.0075 0.0710 1.0000 9.250 1.1031 0.02169 0.01397 -0.0077 0.0629 1.0000 9.500 1.1246 0.02268 0.01497 -0.0078 0.0558 1.0000 9.750 1.1462 0.02358 0.01596 -0.0079 0.0493 1.0000 10.000 1.1659 0.02467 0.01712 -0.0080 0.0436 1.0000 10.250 1.1850 0.02574 0.01825 -0.0080 0.0382 1.0000 10.500 1.2020 0.02696 0.01956 -0.0079 0.0338 1.0000 10.750 1.2182 0.02817 0.02085 -0.0078 0.0297 1.0000 11.000 1.2305 0.02965 0.02240 -0.0075 0.0265 1.0000 11.250 1.2407 0.03101 0.02389 -0.0066 0.0238 1.0000 11.500 1.2473 0.03272 0.02568 -0.0058 0.0217 1.0000 11.750 1.2532 0.03459 0.02766 -0.0051 0.0199 1.0000 12.000 1.2598 0.03644 0.02965 -0.0045 0.0182 1.0000 12.250 1.2646 0.03852 0.03183 -0.0042 0.0168 1.0000 12.500 1.2644 0.04120 0.03458 -0.0040 0.0157 1.0000 12.750 1.2670 0.04367 0.03724 -0.0039 0.0148 1.0000 13.000 1.2671 0.04651 0.04025 -0.0041 0.0141 1.0000 13.250 1.2656 0.04963 0.04352 -0.0045 0.0135 1.0000 13.500 1.2627 0.05306 0.04709 -0.0052 0.0130 1.0000 13.750 1.2581 0.05684 0.05102 -0.0063 0.0126 1.0000 14.000 1.2515 0.06105 0.05537 -0.0077 0.0123 1.0000 14.250 1.2429 0.06577 0.06022 -0.0095 0.0121 1.0000 14.500 1.2325 0.07101 0.06560 -0.0117 0.0118 1.0000 14.750 1.2207 0.07668 0.07141 -0.0143 0.0117 1.0000 15.000 1.2102 0.08241 0.07730 -0.0169 0.0116 1.0000 15.250 1.1987 0.08851 0.08358 -0.0198 0.0114 1.0000 15.500 1.1862 0.09498 0.09021 -0.0230 0.0113 1.0000 15.750 1.1729 0.10177 0.09715 -0.0264 0.0113 1.0000 16.000 1.1591 0.10880 0.10433 -0.0299 0.0112 1.0000 16.250 1.1447 0.11611 0.11179 -0.0337 0.0112 1.0000 16.500 1.1301 0.12368 0.11950 -0.0376 0.0111 1.0000 16.750 1.1149 0.13154 0.12750 -0.0418 0.0111 1.0000 17.000 1.0997 0.13974 0.13583 -0.0462 0.0111 1.0000 17.250 1.0840 0.14839 0.14461 -0.0509 0.0111 1.0000 17.500 1.0672 0.15769 0.15403 -0.0561 0.0112 1.0000 17.750 1.0477 0.16835 0.16481 -0.0621 0.0112 1.0000 18.000 1.0202 0.18257 0.17913 -0.0699 0.0114 1.0000