XFOIL Version 6.96 Calculated polar for: USA 34 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 ------ -------- --------- --------- -------- -------- -------- -19.000 -0.3492 0.14534 0.14326 -0.0810 0.9929 0.0230 -18.750 -0.4316 0.12562 0.12332 -0.0911 0.9919 0.0240 -18.500 -0.4461 0.11826 0.11587 -0.0961 0.9904 0.0244 -18.250 -0.4538 0.11196 0.10949 -0.1008 0.9890 0.0248 -18.000 -0.4562 0.10654 0.10400 -0.1053 0.9876 0.0251 -17.750 -0.4602 0.10078 0.09817 -0.1101 0.9862 0.0255 -17.500 -0.4619 0.09525 0.09255 -0.1151 0.9849 0.0258 -17.250 -0.4587 0.09054 0.08778 -0.1197 0.9837 0.0259 -17.000 -0.4562 0.08565 0.08283 -0.1248 0.9825 0.0263 -16.750 -0.4409 0.08284 0.08002 -0.1286 0.9816 0.0266 -16.500 -0.4438 0.07999 0.07717 -0.1289 0.9749 0.0269 -16.250 -0.4375 0.07630 0.07346 -0.1326 0.9710 0.0271 -16.000 -0.4451 0.07282 0.06996 -0.1336 0.9588 0.0273 -15.750 -0.4463 0.06879 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0.8082 0.01111 0.00470 -0.0755 0.4655 0.2869 3.500 0.8273 0.01131 0.00490 -0.0740 0.4609 0.3013 4.000 0.8712 0.01163 0.00529 -0.0721 0.4545 0.3327 4.250 0.8959 0.01173 0.00545 -0.0718 0.4517 0.3502 4.500 0.9196 0.01187 0.00565 -0.0713 0.4482 0.3714 4.750 0.9441 0.01203 0.00590 -0.0711 0.4442 0.4072 5.000 1.2150 0.01159 0.00673 -0.1242 0.4327 1.0000 5.250 1.2338 0.01181 0.00694 -0.1227 0.4294 1.0000 5.500 1.2512 0.01208 0.00720 -0.1209 0.4256 1.0000 5.750 1.2661 0.01244 0.00752 -0.1188 0.4211 1.0000 6.000 1.2852 0.01269 0.00777 -0.1174 0.4183 1.0000 6.250 1.3053 0.01291 0.00801 -0.1162 0.4152 1.0000 6.500 1.3238 0.01319 0.00829 -0.1148 0.4113 1.0000 6.750 1.3391 0.01358 0.00866 -0.1129 0.4067 1.0000 7.000 1.3534 0.01403 0.00908 -0.1109 0.4018 1.0000 7.250 1.3732 0.01430 0.00938 -0.1098 0.3984 1.0000 7.500 1.3906 0.01467 0.00974 -0.1083 0.3936 1.0000 7.750 1.4052 0.01515 0.01021 -0.1065 0.3884 1.0000 8.000 1.4194 0.01568 0.01072 -0.1046 0.3836 1.0000 8.250 1.4379 0.01604 0.01110 -0.1035 0.3792 1.0000 8.500 1.4539 0.01653 0.01159 -0.1020 0.3747 1.0000 8.750 1.4665 0.01717 0.01222 -0.1001 0.3694 1.0000 9.000 1.4827 0.01769 0.01274 -0.0987 0.3650 1.0000 9.250 1.4982 0.01824 0.01331 -0.0973 0.3593 1.0000 9.500 1.5116 0.01891 0.01397 -0.0957 0.3541 1.0000 9.750 1.5242 0.01965 0.01470 -0.0940 0.3489 1.0000 10.000 1.5393 0.02027 0.01533 -0.0927 0.3424 1.0000 10.250 1.5503 0.02113 0.01618 -0.0909 0.3362 1.0000 10.500 1.5632 0.02191 0.01696 -0.0894 0.3302 1.0000 10.750 1.5759 0.02271 0.01776 -0.0879 0.3234 1.0000 11.000 1.5837 0.02382 0.01885 -0.0860 0.3158 1.0000 11.250 1.5955 0.02470 0.01973 -0.0845 0.3077 1.0000 11.500 1.6016 0.02597 0.02097 -0.0825 0.2990 1.0000 11.750 1.6094 0.02716 0.02214 -0.0807 0.2885 1.0000 12.000 1.6141 0.02859 0.02354 -0.0787 0.2775 1.0000 12.250 1.6145 0.03032 0.02521 -0.0764 0.2632 1.0000 12.500 1.6128 0.03225 0.02707 -0.0740 0.2476 1.0000 12.750 1.6089 0.03442 0.02918 -0.0715 0.2318 1.0000 13.000 1.6045 0.03667 0.03136 -0.0692 0.2165 1.0000 13.250 1.6002 0.03898 0.03363 -0.0669 0.2035 1.0000 13.500 1.5976 0.04125 0.03586 -0.0650 0.1939 1.0000 13.750 1.5996 0.04318 0.03779 -0.0634 0.1867 1.0000 14.000 1.5976 0.04551 0.04012 -0.0618 0.1804 1.0000 14.250 1.6013 0.04736 0.04199 -0.0605 0.1759 1.0000 14.500 1.6043 0.04936 0.04402 -0.0593 0.1727 1.0000 14.750 1.6068 0.05139 0.04607 -0.0582 0.1693 1.0000 15.000 1.6042 0.05398 0.04868 -0.0569 0.1650 1.0000 15.250 1.6095 0.05582 0.05057 -0.0560 0.1625 1.0000 15.500 1.6123 0.05795 0.05275 -0.0551 0.1598 1.0000 15.750 1.6146 0.06014 0.05498 -0.0543 0.1572 1.0000 16.000 1.6140 0.06268 0.05755 -0.0534 0.1547 1.0000 16.250 1.6084 0.06578 0.06068 -0.0524 0.1506 1.0000 16.500 1.6142 0.06767 0.06263 -0.0519 0.1490 1.0000 16.750 1.6166 0.06997 0.06498 -0.0513 0.1460 1.0000 17.000 1.6167 0.07250 0.06755 -0.0507 0.1427 1.0000 17.250 1.6092 0.07594 0.07101 -0.0501 0.1382 1.0000 17.500 1.6120 0.07823 0.07335 -0.0497 0.1346 1.0000 17.750 1.6090 0.08120 0.07635 -0.0493 0.1295 1.0000 18.000 1.6018 0.08466 0.07981 -0.0488 0.1228 1.0000 18.250 1.5939 0.08821 0.08335 -0.0484 0.1146 1.0000 18.500 1.5816 0.09237 0.08748 -0.0482 0.1048 1.0000 18.750 1.5739 0.09599 0.09110 -0.0480 0.0989 1.0000