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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.6829 0.10475 0.10275 0.0459 0.8389 0.0193 -8.750 -0.6839 0.10078 0.09878 0.0450 0.8368 0.0196 -8.500 -0.6831 0.09709 0.09509 0.0437 0.8349 0.0198 -8.250 -0.6830 0.09309 0.09108 0.0417 0.8332 0.0200 -8.000 -0.6822 0.08859 0.08660 0.0382 0.8295 0.0203 -7.750 -0.6835 0.08358 0.08159 0.0336 0.8260 0.0205 -7.500 -0.6798 0.07682 0.07480 0.0262 0.8233 0.0208 -7.250 -0.6746 0.06892 0.06678 0.0181 0.8210 0.0212 -7.000 -0.6676 0.06220 0.05989 0.0135 0.8190 0.0218 -6.750 -0.6568 0.05516 0.05260 0.0096 0.8160 0.0230 -6.500 -0.6617 0.03612 0.03223 0.0067 0.8134 0.0194 -6.250 -0.6412 0.03304 0.02900 0.0070 0.8103 0.0183 -6.000 -0.6227 0.02831 0.02372 0.0077 0.8078 0.0182 -5.750 -0.6020 0.02418 0.01901 0.0087 0.8055 0.0180 -5.500 -0.5777 0.02172 0.01612 0.0095 0.8029 0.0184 -5.250 -0.5499 0.02051 0.01464 0.0097 0.7988 0.0189 -5.000 -0.5252 0.01764 0.01147 0.0102 0.7954 0.0199 -4.750 -0.4989 0.01681 0.01056 0.0106 0.7923 0.0209 -4.500 -0.4722 0.01634 0.01002 0.0110 0.7896 0.0224 -4.250 -0.4436 0.01576 0.00935 0.0110 0.7856 0.0240 -4.000 -0.4153 0.01524 0.00873 0.0112 0.7814 0.0249 -3.750 -0.3894 0.01371 0.00710 0.0117 0.7780 0.0268 -3.500 -0.3623 0.01327 0.00663 0.0120 0.7750 0.0289 -3.250 -0.3334 0.01290 0.00622 0.0119 0.7707 0.0314 -3.000 -0.3047 0.01256 0.00583 0.0120 0.7662 0.0329 -2.750 -0.2775 0.01167 0.00488 0.0122 0.7626 0.0370 -2.500 -0.2498 0.01138 0.00453 0.0125 0.7594 0.0413 -2.250 -0.2202 0.01092 0.00406 0.0123 0.7542 0.0476 -2.000 -0.1915 0.01062 0.00373 0.0123 0.7498 0.0557 -1.750 -0.1636 0.01010 0.00335 0.0124 0.7461 0.0916 -1.500 -0.1356 0.00924 0.00308 0.0120 0.7415 0.2464 -1.250 -0.1083 0.00836 0.00294 0.0118 0.7363 0.4483 -1.000 -0.0810 0.00804 0.00284 0.0121 0.7313 0.5336 -0.750 -0.0526 0.00784 0.00276 0.0122 0.7234 0.5824 -0.500 -0.0248 0.00769 0.00264 0.0126 0.7160 0.6170 -0.250 0.0041 0.00760 0.00259 0.0126 0.7089 0.6456 0.000 0.0325 0.00749 0.00251 0.0127 0.7026 0.6718 0.250 0.0609 0.00737 0.00244 0.0128 0.6962 0.6987 0.500 0.0896 0.00724 0.00236 0.0128 0.6890 0.7217 0.750 0.1176 0.00706 0.00225 0.0129 0.6822 0.7481 1.000 0.1449 0.00633 0.00218 0.0138 0.6744 0.8895 1.250 0.1914 0.00636 0.00215 0.0099 0.6661 1.0000 1.500 0.2200 0.00638 0.00210 0.0099 0.6573 1.0000 1.750 0.2488 0.00640 0.00207 0.0098 0.6478 1.0000 2.000 0.2774 0.00644 0.00204 0.0097 0.6379 1.0000 2.250 0.3061 0.00649 0.00202 0.0097 0.6267 1.0000 2.500 0.3351 0.00653 0.00204 0.0095 0.6147 1.0000 2.750 0.3640 0.00659 0.00205 0.0094 0.6027 1.0000 3.000 0.3930 0.00667 0.00208 0.0092 0.5899 1.0000 3.250 0.4221 0.00675 0.00212 0.0090 0.5751 1.0000 3.500 0.4514 0.00684 0.00217 0.0088 0.5590 1.0000 3.750 0.4808 0.00696 0.00223 0.0084 0.5394 1.0000 4.000 0.5104 0.00711 0.00231 0.0080 0.5165 1.0000 4.250 0.5403 0.00731 0.00242 0.0075 0.4871 1.0000 4.500 0.5707 0.00758 0.00256 0.0068 0.4495 1.0000 4.750 0.6015 0.00794 0.00274 0.0059 0.4062 1.0000 5.000 0.6322 0.00836 0.00299 0.0048 0.3657 1.0000 5.250 0.6627 0.00877 0.00326 0.0039 0.3312 1.0000 5.500 0.6929 0.00918 0.00354 0.0030 0.3012 1.0000 5.750 0.7227 0.00955 0.00382 0.0022 0.2760 1.0000 6.000 0.7523 0.00990 0.00410 0.0015 0.2551 1.0000 6.250 0.7817 0.01027 0.00440 0.0008 0.2355 1.0000 6.500 0.8109 0.01061 0.00470 0.0002 0.2158 1.0000 6.750 0.8400 0.01104 0.00504 -0.0005 0.1940 1.0000 7.000 0.8688 0.01145 0.00539 -0.0012 0.1751 1.0000 7.250 0.8975 0.01187 0.00576 -0.0018 0.1582 1.0000 7.500 0.9259 0.01232 0.00617 -0.0024 0.1416 1.0000 7.750 0.9540 0.01280 0.00661 -0.0030 0.1262 1.0000 8.000 0.9818 0.01331 0.00707 -0.0036 0.1111 1.0000 8.250 1.0093 0.01387 0.00758 -0.0042 0.0965 1.0000 8.500 1.0364 0.01446 0.00813 -0.0047 0.0835 1.0000 8.750 1.0631 0.01506 0.00871 -0.0052 0.0724 1.0000 9.000 1.0894 0.01566 0.00930 -0.0057 0.0623 1.0000 9.250 1.1151 0.01632 0.00994 -0.0061 0.0538 1.0000 9.500 1.1400 0.01714 0.01072 -0.0066 0.0456 1.0000 9.750 1.1653 0.01769 0.01133 -0.0069 0.0406 1.0000 10.000 1.1891 0.01855 0.01221 -0.0073 0.0350 1.0000 10.250 1.2131 0.01926 0.01295 -0.0076 0.0303 1.0000 10.500 1.2356 0.02022 0.01396 -0.0079 0.0257 1.0000 10.750 1.2550 0.02156 0.01530 -0.0083 0.0209 1.0000 11.000 1.2761 0.02248 0.01631 -0.0085 0.0180 1.0000 11.250 1.2900 0.02425 0.01814 -0.0087 0.0154 1.0000 11.500 1.3061 0.02548 0.01948 -0.0086 0.0140 1.0000 11.750 1.3166 0.02691 0.02098 -0.0080 0.0129 1.0000 12.000 1.3193 0.02896 0.02310 -0.0070 0.0121 1.0000 12.250 1.3192 0.03140 0.02567 -0.0061 0.0115 1.0000 12.500 1.3272 0.03313 0.02752 -0.0056 0.0111 1.0000 12.750 1.3328 0.03513 0.02964 -0.0052 0.0106 1.0000 13.000 1.3372 0.03732 0.03194 -0.0050 0.0102 1.0000 13.250 1.3399 0.03975 0.03448 -0.0050 0.0099 1.0000 13.500 1.3406 0.04248 0.03733 -0.0051 0.0096 1.0000 13.750 1.3394 0.04553 0.04049 -0.0054 0.0094 1.0000 14.000 1.3361 0.04895 0.04402 -0.0060 0.0092 1.0000 14.250 1.3302 0.05280 0.04799 -0.0069 0.0090 1.0000 14.500 1.3224 0.05706 0.05238 -0.0081 0.0089 1.0000 14.750 1.3130 0.06172 0.05718 -0.0095 0.0088 1.0000 15.000 1.3020 0.06680 0.06240 -0.0112 0.0087 1.0000 15.250 1.2903 0.07218 0.06792 -0.0132 0.0086 1.0000 15.500 1.2777 0.07789 0.07378 -0.0155 0.0086 1.0000 15.750 1.2639 0.08399 0.08003 -0.0180 0.0085 1.0000 16.000 1.2532 0.08987 0.08605 -0.0208 0.0085 1.0000 16.250 1.2418 0.09607 0.09240 -0.0238 0.0085 1.0000 16.500 1.2294 0.10257 0.09903 -0.0270 0.0085 1.0000 16.750 1.2160 0.10938 0.10598 -0.0304 0.0085 1.0000 17.000 1.2023 0.11643 0.11316 -0.0340 0.0084 1.0000 17.250 1.1880 0.12374 0.12060 -0.0378 0.0084 1.0000 17.500 1.1732 0.13130 0.12829 -0.0418 0.0085 1.0000 17.750 1.1582 0.13921 0.13633 -0.0462 0.0085 1.0000 18.000 1.1427 0.14748 0.14472 -0.0509 0.0085 1.0000