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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.7228 0.11757 0.11534 0.0623 0.8097 0.0076 -9.750 -0.7295 0.11097 0.10874 0.0593 0.8078 0.0077 -8.750 -0.9145 0.03054 0.02642 0.0111 0.7995 0.0077 -8.500 -0.8987 0.02698 0.02238 0.0115 0.7967 0.0080 -8.250 -0.8762 0.02555 0.02076 0.0117 0.7939 0.0082 -8.000 -0.8518 0.02472 0.01980 0.0120 0.7914 0.0085 -7.750 -0.8274 0.02388 0.01880 0.0122 0.7891 0.0088 -7.500 -0.8023 0.02276 0.01751 0.0124 0.7860 0.0092 -7.250 -0.7776 0.02136 0.01587 0.0127 0.7828 0.0096 -7.000 -0.7528 0.01995 0.01419 0.0131 0.7798 0.0100 -6.750 -0.7274 0.01879 0.01278 0.0134 0.7771 0.0104 -6.500 -0.7014 0.01788 0.01165 0.0138 0.7746 0.0107 -6.250 -0.6752 0.01681 0.01047 0.0140 0.7713 0.0112 -6.000 -0.6480 0.01622 0.00982 0.0140 0.7678 0.0117 -5.750 -0.6207 0.01568 0.00920 0.0142 0.7645 0.0122 -5.500 -0.5935 0.01512 0.00854 0.0144 0.7615 0.0129 -5.250 -0.5661 0.01460 0.00790 0.0145 0.7586 0.0136 -5.000 -0.5378 0.01421 0.00743 0.0145 0.7548 0.0144 -4.750 -0.5103 0.01357 0.00675 0.0146 0.7510 0.0155 -4.500 -0.4824 0.01318 0.00632 0.0147 0.7475 0.0164 -4.250 -0.4545 0.01278 0.00584 0.0148 0.7445 0.0174 -4.000 -0.4259 0.01241 0.00542 0.0147 0.7403 0.0185 -3.750 -0.3975 0.01199 0.00496 0.0147 0.7360 0.0201 -3.500 -0.3692 0.01168 0.00462 0.0147 0.7322 0.0217 -3.250 -0.3407 0.01139 0.00428 0.0147 0.7286 0.0234 -3.000 -0.3117 0.01114 0.00399 0.0146 0.7238 0.0250 -2.750 -0.2830 0.01081 0.00365 0.0146 0.7192 0.0283 -2.500 -0.2544 0.01060 0.00340 0.0146 0.7152 0.0317 -2.250 -0.2253 0.01036 0.00314 0.0144 0.7103 0.0359 -2.000 -0.1963 0.01015 0.00293 0.0143 0.7051 0.0417 -1.750 -0.1675 0.00993 0.00271 0.0143 0.7005 0.0515 -1.500 -0.1383 0.00969 0.00253 0.0141 0.6952 0.0707 -1.250 -0.1095 0.00932 0.00236 0.0138 0.6896 0.1265 -1.000 -0.0809 0.00894 0.00220 0.0136 0.6834 0.1973 -0.750 -0.0524 0.00843 0.00202 0.0134 0.6726 0.3034 -0.500 -0.0243 0.00793 0.00192 0.0132 0.6604 0.4336 -0.250 0.0043 0.00770 0.00188 0.0131 0.6508 0.5057 0.000 0.0331 0.00755 0.00186 0.0130 0.6423 0.5568 0.500 0.0910 0.00741 0.00184 0.0128 0.6253 0.6254 0.750 0.1203 0.00738 0.00183 0.0126 0.6157 0.6469 1.000 0.1494 0.00733 0.00181 0.0125 0.6064 0.6715 1.250 0.1786 0.00730 0.00179 0.0123 0.5959 0.6919 1.500 0.2080 0.00728 0.00178 0.0121 0.5845 0.7061 2.000 0.2666 0.00723 0.00176 0.0116 0.5577 0.7384 2.250 0.2953 0.00712 0.00175 0.0115 0.5414 0.7698 2.500 0.3207 0.00677 0.00180 0.0125 0.5238 0.9536 2.750 0.3572 0.00690 0.00186 0.0107 0.5025 0.9826 3.000 0.3938 0.00706 0.00193 0.0087 0.4773 0.9959 3.250 0.4263 0.00728 0.00203 0.0076 0.4464 1.0000 3.500 0.4566 0.00754 0.00214 0.0069 0.4121 1.0000 3.750 0.4871 0.00787 0.00230 0.0060 0.3737 1.0000 4.000 0.5174 0.00820 0.00248 0.0052 0.3419 1.0000 4.250 0.5475 0.00850 0.00267 0.0045 0.3147 1.0000 4.500 0.5773 0.00879 0.00286 0.0038 0.2920 1.0000 4.750 0.6069 0.00906 0.00305 0.0032 0.2727 1.0000 5.000 0.6365 0.00933 0.00327 0.0027 0.2548 1.0000 5.250 0.6660 0.00964 0.00349 0.0020 0.2359 1.0000 5.500 0.6954 0.00995 0.00373 0.0014 0.2146 1.0000 5.750 0.7247 0.01029 0.00399 0.0008 0.1944 1.0000 6.000 0.7538 0.01060 0.00425 0.0002 0.1796 1.0000 6.250 0.7828 0.01091 0.00453 -0.0004 0.1658 1.0000 6.500 0.8116 0.01125 0.00483 -0.0009 0.1521 1.0000 6.750 0.8404 0.01167 0.00518 -0.0015 0.1356 1.0000 7.000 0.8689 0.01206 0.00553 -0.0021 0.1219 1.0000 7.250 0.8972 0.01243 0.00588 -0.0026 0.1105 1.0000 7.500 0.9253 0.01285 0.00627 -0.0032 0.0983 1.0000 7.750 0.9532 0.01329 0.00670 -0.0037 0.0874 1.0000 8.000 0.9808 0.01377 0.00714 -0.0042 0.0770 1.0000 8.250 1.0081 0.01428 0.00763 -0.0047 0.0670 1.0000 8.500 1.0351 0.01481 0.00815 -0.0052 0.0582 1.0000 8.750 1.0617 0.01533 0.00867 -0.0056 0.0510 1.0000 9.000 1.0879 0.01593 0.00925 -0.0060 0.0432 1.0000 9.250 1.1134 0.01660 0.00989 -0.0064 0.0360 1.0000 9.500 1.1390 0.01717 0.01049 -0.0068 0.0311 1.0000 9.750 1.1638 0.01785 0.01119 -0.0071 0.0264 1.0000 10.000 1.1882 0.01855 0.01190 -0.0075 0.0226 1.0000 10.250 1.2121 0.01927 0.01267 -0.0078 0.0197 1.0000 10.500 1.2352 0.02008 0.01351 -0.0081 0.0167 1.0000 10.750 1.2575 0.02092 0.01440 -0.0084 0.0143 1.0000 11.000 1.2785 0.02189 0.01542 -0.0086 0.0122 1.0000 11.250 1.2986 0.02288 0.01649 -0.0088 0.0107 1.0000 11.500 1.3168 0.02398 0.01766 -0.0090 0.0094 1.0000 11.750 1.3322 0.02529 0.01903 -0.0089 0.0084 1.0000 12.000 1.3451 0.02650 0.02035 -0.0084 0.0079 1.0000 12.250 1.3552 0.02783 0.02178 -0.0076 0.0074 1.0000 12.500 1.3645 0.02932 0.02336 -0.0070 0.0070 1.0000 12.750 1.3723 0.03099 0.02512 -0.0064 0.0066 1.0000 13.000 1.3776 0.03296 0.02720 -0.0059 0.0062 1.0000 13.250 1.3816 0.03512 0.02947 -0.0056 0.0060 1.0000 13.500 1.3866 0.03722 0.03170 -0.0054 0.0058 1.0000 13.750 1.3901 0.03956 0.03416 -0.0054 0.0056 1.0000 14.000 1.3918 0.04217 0.03689 -0.0055 0.0054 1.0000 14.250 1.3918 0.04506 0.03992 -0.0059 0.0053 1.0000 14.500 1.3896 0.04834 0.04333 -0.0066 0.0052 1.0000 14.750 1.3858 0.05196 0.04708 -0.0075 0.0051 1.0000 15.000 1.3802 0.05599 0.05125 -0.0088 0.0050 1.0000 15.250 1.3729 0.06049 0.05589 -0.0105 0.0049 1.0000 15.500 1.3634 0.06552 0.06107 -0.0125 0.0049 1.0000 15.750 1.3521 0.07110 0.06679 -0.0150 0.0048 1.0000 16.000 1.3383 0.07727 0.07311 -0.0179 0.0048 1.0000 16.250 1.3226 0.08405 0.08004 -0.0211 0.0048 1.0000 16.500 1.3049 0.09135 0.08749 -0.0247 0.0048 1.0000 16.750 1.2855 0.09913 0.09541 -0.0285 0.0048 1.0000 17.000 1.2654 0.10717 0.10359 -0.0324 0.0048 1.0000 17.250 1.2447 0.11538 0.11193 -0.0364 0.0048 1.0000