XFOIL Version 6.96 Calculated polar for: HQ 3.0/15 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 ------ -------- --------- --------- -------- -------- -------- -16.750 -0.6994 0.10462 0.10151 -0.0540 1.0000 0.0096 -16.500 -0.7504 0.09126 0.08798 -0.0611 1.0000 0.0095 -16.250 -0.7954 0.07924 0.07579 -0.0679 1.0000 0.0093 -16.000 -0.8296 0.06921 0.06557 -0.0739 1.0000 0.0093 -15.750 -0.8564 0.06091 0.05709 -0.0791 1.0000 0.0092 -15.500 -0.8762 0.05457 0.05059 -0.0829 1.0000 0.0092 -15.250 -0.8899 0.04964 0.04553 -0.0855 1.0000 0.0092 -15.000 -0.8995 0.04561 0.04137 -0.0874 1.0000 0.0093 -14.750 -0.9077 0.04201 0.03766 -0.0887 1.0000 0.0094 -14.500 -0.9125 0.03906 0.03459 -0.0894 1.0000 0.0094 -14.250 -0.9161 0.03644 0.03187 -0.0897 1.0000 0.0095 -14.000 -0.9190 0.03410 0.02944 -0.0896 1.0000 0.0096 -13.750 -0.9210 0.03210 0.02735 -0.0889 1.0000 0.0097 -13.500 -0.9232 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1.000 0.5135 0.00815 0.00225 -0.0852 0.6092 0.6413 1.250 0.5410 0.00819 0.00229 -0.0851 0.6003 0.6467 1.500 0.5681 0.00825 0.00233 -0.0850 0.5912 0.6520 1.750 0.5949 0.00833 0.00237 -0.0847 0.5803 0.6569 2.000 0.6211 0.00842 0.00243 -0.0844 0.5660 0.6618 2.250 0.6469 0.00853 0.00250 -0.0840 0.5506 0.6674 2.500 0.6728 0.00865 0.00257 -0.0836 0.5362 0.6730 2.750 0.6982 0.00877 0.00268 -0.0832 0.5211 0.6784 3.000 0.7232 0.00893 0.00278 -0.0826 0.5046 0.6842 3.250 0.7477 0.00911 0.00290 -0.0820 0.4871 0.6897 3.500 0.7717 0.00930 0.00305 -0.0813 0.4697 0.6956 3.750 0.7954 0.00951 0.00320 -0.0806 0.4504 0.7020 4.000 0.8183 0.00976 0.00338 -0.0797 0.4297 0.7078 4.250 0.8408 0.01001 0.00357 -0.0788 0.4103 0.7142 4.750 0.8847 0.01056 0.00401 -0.0768 0.3697 0.7275 5.000 0.9057 0.01088 0.00424 -0.0757 0.3484 0.7346 5.250 0.9260 0.01120 0.00450 -0.0744 0.3284 0.7413 5.500 0.9468 0.01149 0.00476 -0.0732 0.3128 0.7491 5.750 0.9669 0.01179 0.00502 -0.0720 0.2986 0.7567 6.000 0.9868 0.01209 0.00530 -0.0706 0.2848 0.7650 6.250 1.0066 0.01237 0.00557 -0.0693 0.2735 0.7729 6.500 1.0248 0.01263 0.00585 -0.0676 0.2641 0.7823 6.750 1.0420 0.01290 0.00612 -0.0658 0.2544 0.7919 7.000 1.0595 0.01318 0.00643 -0.0640 0.2449 0.8027 7.250 1.0755 0.01351 0.00677 -0.0620 0.2348 0.8148 7.500 1.0916 0.01382 0.00711 -0.0601 0.2242 0.8291 7.750 1.1074 0.01413 0.00746 -0.0581 0.2146 0.8474 8.250 1.1514 0.01481 0.00830 -0.0571 0.1931 1.0000 8.500 1.1683 0.01526 0.00873 -0.0556 0.1846 1.0000 8.750 1.1835 0.01579 0.00923 -0.0539 0.1758 1.0000 9.000 1.1987 0.01633 0.00975 -0.0523 0.1661 1.0000 9.250 1.2141 0.01689 0.01029 -0.0508 0.1588 1.0000 9.500 1.2269 0.01759 0.01094 -0.0490 0.1481 1.0000 9.750 1.2432 0.01814 0.01150 -0.0477 0.1421 1.0000 10.000 1.2563 0.01887 0.01220 -0.0461 0.1339 1.0000 10.250 1.2708 0.01955 0.01288 -0.0446 0.1260 1.0000 10.500 1.2838 0.02033 0.01364 -0.0431 0.1190 1.0000 10.750 1.2972 0.02111 0.01442 -0.0417 0.1116 1.0000 11.000 1.3092 0.02200 0.01528 -0.0403 0.1039 1.0000 11.250 1.3204 0.02296 0.01623 -0.0388 0.0961 1.0000 11.500 1.3313 0.02397 0.01722 -0.0374 0.0872 1.0000 11.750 1.3416 0.02505 0.01828 -0.0360 0.0804 1.0000 12.000 1.3522 0.02614 0.01937 -0.0347 0.0739 1.0000 12.250 1.3619 0.02731 0.02055 -0.0334 0.0684 1.0000 12.500 1.3713 0.02854 0.02178 -0.0321 0.0628 1.0000 12.750 1.3800 0.02985 0.02310 -0.0309 0.0579 1.0000 13.000 1.3877 0.03126 0.02453 -0.0298 0.0527 1.0000 13.250 1.3956 0.03271 0.02599 -0.0287 0.0486 1.0000 13.500 1.4035 0.03419 0.02751 -0.0277 0.0450 1.0000 13.750 1.4089 0.03591 0.02924 -0.0267 0.0409 1.0000 14.000 1.4160 0.03755 0.03092 -0.0258 0.0378 1.0000 14.250 1.4199 0.03953 0.03290 -0.0250 0.0342 1.0000 14.500 1.4256 0.04139 0.03483 -0.0243 0.0312 1.0000 14.750 1.4286 0.04356 0.03702 -0.0237 0.0281 1.0000 15.000 1.4342 0.04555 0.03907 -0.0232 0.0263 1.0000 15.250 1.4389 0.04769 0.04128 -0.0228 0.0248 1.0000 15.500 1.4396 0.05029 0.04392 -0.0225 0.0218 1.0000 15.750 1.4428 0.05270 0.04640 -0.0223 0.0202 1.0000 16.000 1.4422 0.05562 0.04937 -0.0223 0.0176 1.0000 16.250 1.4416 0.05864 0.05245 -0.0224 0.0154 1.0000 16.500 1.4372 0.06219 0.05605 -0.0227 0.0123 1.0000 16.750 1.4339 0.06572 0.05966 -0.0232 0.0102 1.0000 17.000 1.4222 0.07050 0.06448 -0.0241 0.0064 1.0000 17.250 1.4155 0.07476 0.06884 -0.0251 0.0055 1.0000 17.500 1.4101 0.07896 0.07314 -0.0262 0.0052 1.0000 17.750 1.4017 0.08373 0.07802 -0.0276 0.0048 1.0000 18.000 1.3951 0.08836 0.08276 -0.0292 0.0047 1.0000 18.250 1.3850 0.09363 0.08814 -0.0311 0.0044 1.0000 18.500 1.3791 0.09834 0.09297 -0.0330 0.0044 1.0000 18.750 1.3703 0.10360 0.09836 -0.0351 0.0043 1.0000