XFOIL Version 6.96 Calculated polar for: NACA 63-415 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 -0.8646 0.12321 0.12092 -0.0296 1.0000 0.0126 -18.750 -0.9113 0.10995 0.10745 -0.0369 1.0000 0.0125 -18.500 -0.9426 0.10016 0.09750 -0.0423 1.0000 0.0125 -18.250 -0.9666 0.09203 0.08924 -0.0468 1.0000 0.0125 -18.000 -0.9822 0.08548 0.08257 -0.0505 1.0000 0.0125 -17.750 -0.9996 0.07888 0.07585 -0.0541 1.0000 0.0125 -17.500 -1.0116 0.07328 0.07015 -0.0573 1.0000 0.0126 -17.250 -1.0199 0.06841 0.06518 -0.0599 1.0000 0.0127 -17.000 -1.0288 0.06362 0.06029 -0.0625 1.0000 0.0129 -16.750 -1.0375 0.05907 0.05562 -0.0649 1.0000 0.0129 -16.500 -1.0407 0.05535 0.05182 -0.0668 1.0000 0.0130 -16.250 -1.0452 0.05161 0.04798 -0.0685 1.0000 0.0132 -16.000 -1.0464 0.04846 0.04474 -0.0699 1.0000 0.0133 -15.750 -1.0484 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0.5291 0.6840 3.750 0.7816 0.00709 0.00227 -0.0821 0.5097 0.6972 4.000 0.8095 0.00721 0.00237 -0.0822 0.4970 0.7044 4.250 0.8374 0.00731 0.00247 -0.0823 0.4831 0.7109 4.500 0.8647 0.00746 0.00259 -0.0822 0.4666 0.7177 4.750 0.8923 0.00761 0.00272 -0.0823 0.4520 0.7246 5.000 0.9195 0.00775 0.00287 -0.0822 0.4371 0.7315 5.250 0.9461 0.00797 0.00304 -0.0821 0.4182 0.7387 5.500 0.9719 0.00823 0.00323 -0.0819 0.3925 0.7454 5.750 0.9960 0.00862 0.00350 -0.0814 0.3566 0.7528 6.000 1.0185 0.00916 0.00385 -0.0807 0.3119 0.7600 6.250 1.0392 0.00982 0.00429 -0.0798 0.2631 0.7675 6.500 1.0583 0.01059 0.00480 -0.0786 0.2094 0.7753 6.750 1.0769 0.01135 0.00533 -0.0774 0.1628 0.7835 7.000 1.0957 0.01206 0.00584 -0.0762 0.1257 0.7919 7.250 1.1149 0.01268 0.00634 -0.0750 0.0971 0.8007 7.500 1.1338 0.01330 0.00685 -0.0738 0.0744 0.8099 7.750 1.1524 0.01388 0.00735 -0.0725 0.0574 0.8199 8.000 1.1711 0.01442 0.00785 -0.0712 0.0467 0.8296 8.250 1.1905 0.01487 0.00831 -0.0700 0.0414 0.8404 8.500 1.2091 0.01530 0.00878 -0.0686 0.0378 0.8521 8.750 1.2265 0.01572 0.00924 -0.0671 0.0351 0.8646 9.000 1.2385 0.01621 0.00978 -0.0645 0.0325 0.8800 9.250 1.2521 0.01656 0.01022 -0.0622 0.0313 0.8995 9.500 1.2612 0.01693 0.01070 -0.0591 0.0299 0.9304 9.750 1.2714 0.01744 0.01128 -0.0566 0.0284 1.0000 10.000 1.2843 0.01817 0.01203 -0.0548 0.0269 1.0000 10.250 1.3000 0.01876 0.01266 -0.0536 0.0258 1.0000 10.500 1.3140 0.01948 0.01340 -0.0522 0.0246 1.0000 10.750 1.3241 0.02045 0.01438 -0.0504 0.0231 1.0000 11.000 1.3359 0.02137 0.01534 -0.0489 0.0222 1.0000 11.250 1.3496 0.02220 0.01621 -0.0478 0.0211 1.0000 11.500 1.3619 0.02314 0.01718 -0.0465 0.0203 1.0000 11.750 1.3703 0.02441 0.01847 -0.0451 0.0192 1.0000 12.000 1.3779 0.02579 0.01990 -0.0437 0.0184 1.0000 12.250 1.3901 0.02687 0.02103 -0.0427 0.0178 1.0000 12.500 1.4013 0.02806 0.02227 -0.0418 0.0172 1.0000 12.750 1.4120 0.02932 0.02355 -0.0409 0.0166 1.0000 13.000 1.4201 0.03083 0.02511 -0.0400 0.0160 1.0000 13.250 1.4228 0.03285 0.02718 -0.0389 0.0154 1.0000 13.500 1.4282 0.03471 0.02911 -0.0380 0.0151 1.0000 13.750 1.4362 0.03638 0.03085 -0.0374 0.0148 1.0000 14.000 1.4436 0.03815 0.03269 -0.0368 0.0145 1.0000 14.250 1.4493 0.04014 0.03474 -0.0363 0.0142 1.0000 14.500 1.4557 0.04211 0.03677 -0.0359 0.0140 1.0000 14.750 1.4609 0.04425 0.03898 -0.0356 0.0137 1.0000 15.000 1.4656 0.04654 0.04133 -0.0354 0.0134 1.0000 15.250 1.4693 0.04899 0.04384 -0.0354 0.0132 1.0000 15.500 1.4713 0.05169 0.04660 -0.0354 0.0129 1.0000 15.750 1.4711 0.05476 0.04975 -0.0356 0.0128 1.0000 16.000 1.4672 0.05838 0.05345 -0.0360 0.0125 1.0000 16.250 1.4596 0.06257 0.05774 -0.0366 0.0123 1.0000 16.500 1.4621 0.06558 0.06084 -0.0371 0.0122 1.0000 16.750 1.4631 0.06888 0.06423 -0.0379 0.0121 1.0000 17.000 1.4646 0.07218 0.06762 -0.0387 0.0120 1.0000 17.250 1.4640 0.07582 0.07136 -0.0397 0.0119 1.0000 17.500 1.4634 0.07955 0.07518 -0.0408 0.0118 1.0000 17.750 1.4626 0.08339 0.07911 -0.0421 0.0116 1.0000 18.000 1.4611 0.08742 0.08324 -0.0436 0.0115 1.0000 18.250 1.4582 0.09172 0.08764 -0.0452 0.0114 1.0000 18.500 1.4555 0.09609 0.09209 -0.0469 0.0112 1.0000 18.750 1.4518 0.10066 0.09676 -0.0488 0.0111 1.0000 19.000 1.4477 0.10540 0.10159 -0.0509 0.0110 1.0000 19.250 1.4429 0.11030 0.10659 -0.0532 0.0109 1.0000