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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.5553 0.13002 0.12835 0.0516 0.8099 0.0115 -10.500 -0.5549 0.12640 0.12473 0.0506 0.8081 0.0116 -8.250 -0.8715 0.03023 0.02695 0.0126 0.8019 0.0087 -8.000 -0.8543 0.02678 0.02310 0.0130 0.7992 0.0090 -7.750 -0.8341 0.02409 0.02006 0.0135 0.7964 0.0092 -7.500 -0.8120 0.02191 0.01756 0.0140 0.7937 0.0094 -7.250 -0.7884 0.02015 0.01552 0.0145 0.7911 0.0097 -7.000 -0.7637 0.01874 0.01386 0.0149 0.7884 0.0100 -6.750 -0.7376 0.01763 0.01259 0.0152 0.7856 0.0103 -6.500 -0.7106 0.01697 0.01178 0.0154 0.7825 0.0106 -6.250 -0.6861 0.01514 0.00972 0.0159 0.7795 0.0114 -6.000 -0.6588 0.01471 0.00924 0.0160 0.7767 0.0119 -5.750 -0.6314 0.01425 0.00871 0.0161 0.7738 0.0125 -5.500 -0.6036 0.01372 0.00812 0.0162 0.7707 0.0131 -5.250 -0.5757 0.01320 0.00752 0.0164 0.7673 0.0137 -5.000 -0.5477 0.01284 0.00709 0.0165 0.7641 0.0142 -4.750 -0.5209 0.01181 0.00593 0.0168 0.7610 0.0153 -4.500 -0.4927 0.01145 0.00556 0.0168 0.7577 0.0163 -4.250 -0.4642 0.01114 0.00523 0.0168 0.7540 0.0173 -4.000 -0.4356 0.01090 0.00495 0.0168 0.7502 0.0184 -3.750 -0.4073 0.01053 0.00451 0.0168 0.7467 0.0195 -3.500 -0.3790 0.01005 0.00399 0.0168 0.7431 0.0214 -3.250 -0.3501 0.00980 0.00374 0.0168 0.7390 0.0230 -3.000 -0.3212 0.00961 0.00353 0.0167 0.7347 0.0246 -2.750 -0.2926 0.00924 0.00309 0.0167 0.7308 0.0274 -2.500 -0.2635 0.00903 0.00288 0.0167 0.7265 0.0305 -2.250 -0.2344 0.00888 0.00272 0.0166 0.7216 0.0329 -2.000 -0.2054 0.00858 0.00241 0.0165 0.7170 0.0407 -1.750 -0.1763 0.00838 0.00222 0.0164 0.7117 0.0499 -1.500 -0.1473 0.00809 0.00202 0.0163 0.7039 0.0761 -1.250 -0.1186 0.00761 0.00183 0.0160 0.6952 0.1638 -1.000 -0.0899 0.00712 0.00167 0.0157 0.6871 0.2663 -0.750 -0.0616 0.00652 0.00156 0.0154 0.6805 0.4168 -0.500 -0.0328 0.00625 0.00152 0.0153 0.6734 0.4979 -0.250 -0.0038 0.00612 0.00149 0.0152 0.6664 0.5438 0.000 0.0253 0.00603 0.00147 0.0150 0.6587 0.5786 0.250 0.0545 0.00596 0.00147 0.0149 0.6513 0.6105 0.500 0.0839 0.00593 0.00146 0.0147 0.6429 0.6332 0.750 0.1132 0.00589 0.00146 0.0145 0.6348 0.6558 1.250 0.1720 0.00585 0.00144 0.0141 0.6160 0.6904 1.500 0.2012 0.00580 0.00143 0.0139 0.6057 0.7121 1.750 0.2304 0.00573 0.00142 0.0137 0.5945 0.7389 2.000 0.2587 0.00549 0.00138 0.0137 0.5827 0.7914 2.250 0.2805 0.00509 0.00140 0.0155 0.5717 0.9686 2.500 0.3178 0.00515 0.00143 0.0136 0.5578 0.9907 2.750 0.3554 0.00525 0.00147 0.0114 0.5415 1.0000 3.000 0.3846 0.00535 0.00151 0.0112 0.5245 1.0000 3.250 0.4140 0.00549 0.00157 0.0108 0.5037 1.0000 3.500 0.4436 0.00565 0.00164 0.0104 0.4780 1.0000 3.750 0.4737 0.00587 0.00173 0.0098 0.4444 1.0000 4.000 0.5042 0.00618 0.00186 0.0090 0.4018 1.0000 4.250 0.5347 0.00649 0.00202 0.0082 0.3640 1.0000 4.500 0.5649 0.00678 0.00218 0.0075 0.3332 1.0000 4.750 0.5951 0.00708 0.00236 0.0067 0.3048 1.0000 5.000 0.6252 0.00737 0.00254 0.0060 0.2793 1.0000 5.250 0.6549 0.00762 0.00271 0.0054 0.2585 1.0000 5.500 0.6846 0.00786 0.00289 0.0049 0.2409 1.0000 5.750 0.7142 0.00812 0.00308 0.0043 0.2235 1.0000 6.000 0.7438 0.00839 0.00329 0.0036 0.2062 1.0000 6.250 0.7734 0.00869 0.00351 0.0030 0.1865 1.0000 6.500 0.8029 0.00901 0.00375 0.0023 0.1683 1.0000 6.750 0.8322 0.00932 0.00401 0.0017 0.1533 1.0000 7.000 0.8615 0.00966 0.00429 0.0011 0.1379 1.0000 7.250 0.8905 0.00999 0.00457 0.0004 0.1247 1.0000 7.500 0.9195 0.01035 0.00488 -0.0002 0.1111 1.0000 7.750 0.9483 0.01076 0.00522 -0.0008 0.0967 1.0000 8.000 0.9769 0.01120 0.00559 -0.0015 0.0828 1.0000 8.250 1.0052 0.01167 0.00599 -0.0021 0.0695 1.0000 8.500 1.0333 0.01215 0.00642 -0.0028 0.0584 1.0000 8.750 1.0611 0.01257 0.00683 -0.0033 0.0513 1.0000 9.000 1.0888 0.01304 0.00728 -0.0038 0.0445 1.0000 9.250 1.1160 0.01354 0.00775 -0.0043 0.0389 1.0000 9.500 1.1431 0.01399 0.00822 -0.0048 0.0343 1.0000 9.750 1.1697 0.01456 0.00878 -0.0053 0.0291 1.0000 10.000 1.1961 0.01507 0.00930 -0.0057 0.0253 1.0000 10.250 1.2217 0.01575 0.00996 -0.0061 0.0208 1.0000 10.500 1.2470 0.01638 0.01059 -0.0065 0.0172 1.0000 10.750 1.2716 0.01715 0.01137 -0.0070 0.0135 1.0000 11.000 1.2952 0.01804 0.01230 -0.0074 0.0106 1.0000 11.250 1.3170 0.01920 0.01349 -0.0079 0.0085 1.0000 11.500 1.3400 0.01998 0.01434 -0.0083 0.0078 1.0000 11.750 1.3613 0.02093 0.01535 -0.0086 0.0072 1.0000 12.000 1.3804 0.02207 0.01656 -0.0089 0.0067 1.0000 12.250 1.3943 0.02371 0.01831 -0.0091 0.0062 1.0000 12.500 1.4039 0.02527 0.01998 -0.0086 0.0060 1.0000 12.750 1.4139 0.02660 0.02141 -0.0078 0.0059 1.0000 13.000 1.4231 0.02809 0.02299 -0.0072 0.0058 1.0000 13.250 1.4307 0.02977 0.02477 -0.0067 0.0056 1.0000 13.500 1.4369 0.03164 0.02675 -0.0062 0.0055 1.0000 13.750 1.4416 0.03370 0.02891 -0.0059 0.0054 1.0000 14.000 1.4446 0.03601 0.03132 -0.0057 0.0053 1.0000 14.250 1.4463 0.03854 0.03396 -0.0058 0.0052 1.0000 14.500 1.4458 0.04140 0.03694 -0.0060 0.0052 1.0000 14.750 1.4442 0.04451 0.04016 -0.0065 0.0051 1.0000 15.000 1.4408 0.04795 0.04372 -0.0072 0.0050 1.0000 15.250 1.4353 0.05182 0.04771 -0.0082 0.0050 1.0000 15.500 1.4278 0.05618 0.05219 -0.0097 0.0049 1.0000 15.750 1.4191 0.06093 0.05707 -0.0115 0.0049 1.0000 16.000 1.4077 0.06630 0.06257 -0.0137 0.0049 1.0000 16.250 1.3949 0.07215 0.06856 -0.0163 0.0048 1.0000 16.500 1.3794 0.07859 0.07514 -0.0192 0.0048 1.0000 16.750 1.3618 0.08567 0.08235 -0.0226 0.0048 1.0000 17.000 1.3431 0.09307 0.08988 -0.0261 0.0048 1.0000 17.250 1.3232 0.10081 0.09774 -0.0298 0.0048 1.0000 17.500 1.3022 0.10885 0.10591 -0.0336 0.0049 1.0000