XFOIL Version 6.96 Calculated polar for: NACA 66-021 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9099 0.09421 0.09027 -0.0751 0.9590 0.0215 -19.500 -0.9224 0.08742 0.08321 -0.0800 0.9500 0.0216 -19.250 -0.9310 0.08181 0.07737 -0.0834 0.9397 0.0215 -19.000 -0.9393 0.07739 0.07272 -0.0851 0.9276 0.0216 -18.750 -0.9456 0.07373 0.06885 -0.0857 0.9172 0.0215 -18.500 -0.9534 0.07018 0.06510 -0.0860 0.9080 0.0216 -18.250 -0.9582 0.06709 0.06181 -0.0860 0.9004 0.0216 -18.000 -0.9630 0.06409 0.05862 -0.0859 0.8932 0.0217 -17.750 -0.9686 0.06140 0.05572 -0.0855 0.8865 0.0218 -17.500 -0.9699 0.05896 0.05311 -0.0851 0.8809 0.0219 -17.250 -0.9610 0.05686 0.05086 -0.0849 0.8759 0.0220 -17.000 -0.9439 0.05542 0.04933 -0.0849 0.8715 0.0223 -16.750 -0.9306 0.05408 0.04791 -0.0847 0.8669 0.0225 -16.500 -0.9187 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0.7548 2.500 0.2341 0.01635 0.01162 0.0032 0.7256 0.7555 2.750 0.2656 0.01607 0.01134 0.0023 0.7242 0.7560 3.000 0.3006 0.01561 0.01088 0.0008 0.7229 0.7567 3.250 0.3371 0.01517 0.01043 -0.0009 0.7214 0.7573 3.500 0.3637 0.01503 0.01033 -0.0010 0.7184 0.7580 3.750 0.3804 0.01502 0.01039 0.0007 0.7134 0.7588 4.000 0.4160 0.01447 0.00985 -0.0007 0.7096 0.7594 4.250 0.4612 0.01356 0.00890 -0.0036 0.7054 0.7599 4.500 0.4945 0.01308 0.00842 -0.0046 0.6997 0.7605 4.750 0.5207 0.01257 0.00795 -0.0042 0.6913 0.7613 5.000 0.5533 0.01197 0.00732 -0.0049 0.6822 0.7620 5.250 0.5765 0.01164 0.00703 -0.0041 0.6724 0.7629 5.500 0.5996 0.01145 0.00688 -0.0033 0.6639 0.7641 5.750 0.6208 0.01123 0.00667 -0.0022 0.6522 0.7652 6.000 0.6336 0.01112 0.00661 0.0005 0.6358 0.7664 6.250 0.6360 0.01103 0.00652 0.0053 0.6061 0.7677 6.500 0.6191 0.01121 0.00644 0.0137 0.5580 0.7695 6.750 0.5996 0.01211 0.00706 0.0216 0.5113 0.7712 7.000 0.5810 0.01324 0.00794 0.0288 0.4659 0.7728 7.250 0.5677 0.01442 0.00890 0.0347 0.4226 0.7741 7.500 0.5564 0.01558 0.00985 0.0400 0.3796 0.7758 7.750 0.5489 0.01675 0.01081 0.0446 0.3340 0.7774 8.000 0.5420 0.01800 0.01182 0.0489 0.2840 0.7789 8.250 0.5358 0.01931 0.01284 0.0529 0.2262 0.7805 8.500 0.5369 0.02041 0.01368 0.0559 0.1766 0.7820 8.750 0.5364 0.02164 0.01460 0.0589 0.1216 0.7836 9.000 0.5390 0.02280 0.01548 0.0614 0.0781 0.7853 9.250 0.5483 0.02369 0.01624 0.0632 0.0580 0.7869 9.500 0.5609 0.02444 0.01695 0.0645 0.0499 0.7887 9.750 0.5737 0.02521 0.01768 0.0657 0.0453 0.7904 10.000 0.5888 0.02587 0.01834 0.0666 0.0421 0.7920 10.250 0.6009 0.02673 0.01917 0.0678 0.0396 0.7933 10.500 0.6154 0.02738 0.01989 0.0688 0.0376 0.7953 10.750 0.6280 0.02819 0.02072 0.0699 0.0358 0.7972 11.000 0.6386 0.02915 0.02171 0.0712 0.0341 0.7990 11.250 0.6522 0.02996 0.02258 0.0721 0.0332 0.8010 11.500 0.6657 0.03080 0.02345 0.0729 0.0321 0.8030 11.750 0.6775 0.03177 0.02443 0.0739 0.0310 0.8051 12.000 0.6840 0.03308 0.02573 0.0753 0.0299 0.8074 12.250 0.6994 0.03387 0.02658 0.0759 0.0290 0.8095 12.500 0.7120 0.03486 0.02761 0.0767 0.0285 0.8115 12.750 0.7250 0.03579 0.02860 0.0774 0.0281 0.8139 13.000 0.7379 0.03674 0.02960 0.0781 0.0274 0.8165 13.250 0.7501 0.03778 0.03067 0.0788 0.0267 0.8190 13.500 0.7612 0.03891 0.03182 0.0796 0.0261 0.8216 13.750 0.7741 0.03997 0.03289 0.0803 0.0258 0.8243 14.000 0.7880 0.04098 0.03397 0.0808 0.0254 0.8272 14.250 0.8021 0.04201 0.03506 0.0812 0.0252 0.8299 14.500 0.8160 0.04305 0.03619 0.0817 0.0247 0.8329 14.750 0.8301 0.04405 0.03728 0.0822 0.0244 0.8360 15.000 0.8438 0.04512 0.03843 0.0826 0.0241 0.8393 15.250 0.8579 0.04622 0.03960 0.0829 0.0238 0.8428 15.500 0.8706 0.04744 0.04088 0.0833 0.0236 0.8464 15.750 0.8835 0.04866 0.04217 0.0835 0.0233 0.8500 16.000 0.8970 0.04985 0.04346 0.0839 0.0232 0.8540 16.250 0.9078 0.05118 0.04489 0.0842 0.0229 0.8584 16.500 0.9202 0.05253 0.04628 0.0845 0.0226 0.8629 16.750 0.9359 0.05374 0.04749 0.0844 0.0222 0.8670 17.000 0.9444 0.05537 0.04929 0.0848 0.0223 0.8719 17.250 0.9556 0.05695 0.05099 0.0851 0.0222 0.8770 17.500 0.9684 0.05894 0.05309 0.0851 0.0219 0.8816 17.750 0.9722 0.06115 0.05545 0.0854 0.0219 0.8870 18.000 0.9655 0.06398 0.05850 0.0858 0.0217 0.8938 18.250 0.9632 0.06682 0.06152 0.0859 0.0217 0.9008 18.500 0.9565 0.06989 0.06479 0.0860 0.0216 0.9092 18.750 0.9469 0.07363 0.06876 0.0857 0.0215 0.9187 19.000 0.9399 0.07738 0.07273 0.0849 0.0215 0.9298 19.250 0.9306 0.08214 0.07772 0.0829 0.0215 0.9420