XFOIL Version 6.96 Calculated polar for: NACA 0010-66 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 ------ -------- --------- --------- -------- -------- -------- -13.500 -0.6438 0.14346 0.14104 -0.0139 1.0000 0.0259 -13.250 -0.9148 0.06624 0.06364 -0.0512 1.0000 0.0162 -13.000 -0.9452 0.06056 0.05778 -0.0515 1.0000 0.0161 -12.750 -0.9734 0.05646 0.05351 -0.0489 1.0000 0.0160 -12.500 -1.0033 0.05289 0.04975 -0.0443 1.0000 0.0160 -12.250 -1.0333 0.04976 0.04643 -0.0383 1.0000 0.0160 -12.000 -1.0654 0.04685 0.04331 -0.0308 1.0000 0.0161 -11.750 -1.0959 0.04446 0.04070 -0.0224 1.0000 0.0161 -11.500 -1.1254 0.04250 0.03855 -0.0132 1.0000 0.0162 -11.250 -1.1426 0.04036 0.03623 -0.0062 1.0000 0.0164 -11.000 -1.1419 0.03948 0.03530 -0.0019 1.0000 0.0167 -10.750 -1.1335 0.03931 0.03512 0.0012 1.0000 0.0171 -10.500 -1.1263 0.03886 0.03462 0.0045 1.0000 0.0174 -10.250 -1.1188 0.03826 0.03396 0.0078 1.0000 0.0179 -10.000 -1.1167 0.03679 0.03231 0.0120 1.0000 0.0184 -9.750 -1.1162 0.03480 0.03004 0.0166 1.0000 0.0190 -9.500 -1.1140 0.03273 0.02764 0.0212 1.0000 0.0196 -9.250 -1.1067 0.03127 0.02588 0.0249 1.0000 0.0201 -9.000 -1.1006 0.02923 0.02349 0.0288 1.0000 0.0207 -8.750 -1.0811 0.02744 0.02156 0.0296 0.9989 0.0216 -8.500 -1.0598 0.02700 0.02108 0.0304 0.9980 0.0224 -8.250 -1.0386 0.02656 0.02056 0.0313 0.9971 0.0234 -8.000 -1.0176 0.02588 0.01974 0.0324 0.9964 0.0245 -7.750 -0.9943 0.02529 0.01895 0.0331 0.9955 0.0256 -7.500 -0.9711 0.02348 0.01686 0.0337 0.9948 0.0268 -7.250 -0.9452 0.02255 0.01590 0.0336 0.9934 0.0281 -7.000 -0.9231 0.02211 0.01541 0.0345 0.9921 0.0293 -6.750 -0.9009 0.02169 0.01493 0.0354 0.9912 0.0308 -6.500 -0.8780 0.02121 0.01433 0.0363 0.9904 0.0320 -6.250 -0.8546 0.02088 0.01391 0.0371 0.9896 0.0329 -6.000 -0.8314 0.01939 0.01231 0.0378 0.9892 0.0347 -5.750 -0.8080 0.01889 0.01180 0.0384 0.9885 0.0363 -5.500 -0.7822 0.01851 0.01138 0.0386 0.9875 0.0378 -5.250 -0.7552 0.01813 0.01094 0.0386 0.9866 0.0393 -5.000 -0.7288 0.01786 0.01063 0.0387 0.9859 0.0407 -4.750 -0.7026 0.01767 0.01038 0.0388 0.9853 0.0417 -4.500 -0.6787 0.01695 0.00961 0.0395 0.9848 0.0437 -4.250 -0.6526 0.01668 0.00933 0.0397 0.9843 0.0459 -4.000 -0.6326 0.01634 0.00899 0.0412 0.9826 0.0480 -3.750 -0.6121 0.01604 0.00866 0.0426 0.9812 0.0500 -3.500 -0.5884 0.01583 0.00841 0.0434 0.9796 0.0519 -3.250 -0.5657 0.01550 0.00810 0.0444 0.9786 0.0571 -3.000 -0.5419 0.01533 0.00794 0.0451 0.9777 0.0637 -2.750 -0.5186 0.01500 0.00779 0.0459 0.9769 0.0910 -2.500 -0.4950 0.01472 0.00770 0.0465 0.9761 0.1338 -2.250 -0.4695 0.01445 0.00767 0.0466 0.9751 0.1837 -2.000 -0.4436 0.01415 0.00769 0.0467 0.9742 0.2581 -1.750 -0.4202 0.01377 0.00772 0.0472 0.9735 0.3566 -1.500 -0.4044 0.01294 0.00773 0.0494 0.9727 0.5508 -1.250 -0.3734 0.01240 0.00870 0.0496 0.9735 0.9170 -1.000 -0.3385 0.01313 0.00940 0.0484 0.9733 0.9355 -0.750 -0.2957 0.01400 0.01024 0.0454 0.9736 0.9472 -0.500 -0.2020 0.01548 0.01169 0.0312 0.9751 0.9551 -0.250 -0.1393 0.01591 0.01208 0.0238 0.9700 0.9599 0.000 -0.0051 0.01630 0.01246 0.0011 0.9637 0.9634 0.250 0.1382 0.01592 0.01209 -0.0236 0.9600 0.9701 0.500 0.2021 0.01548 0.01169 -0.0313 0.9551 0.9751 0.750 0.2955 0.01400 0.01024 -0.0454 0.9473 0.9737 1.000 0.3384 0.01313 0.00940 -0.0484 0.9355 0.9733 1.250 0.3733 0.01240 0.00870 -0.0496 0.9170 0.9735 1.500 0.4044 0.01293 0.00772 -0.0494 0.5517 0.9727 1.750 0.4201 0.01376 0.00772 -0.0472 0.3569 0.9735 2.000 0.4435 0.01415 0.00769 -0.0466 0.2578 0.9742 2.250 0.4694 0.01445 0.00767 -0.0466 0.1837 0.9751 2.500 0.4949 0.01471 0.00770 -0.0465 0.1341 0.9761 2.750 0.5185 0.01500 0.00778 -0.0458 0.0910 0.9769 3.000 0.5418 0.01533 0.00794 -0.0450 0.0637 0.9777 3.250 0.5656 0.01549 0.00809 -0.0444 0.0571 0.9786 3.500 0.5883 0.01583 0.00841 -0.0434 0.0519 0.9796 3.750 0.6120 0.01604 0.00866 -0.0426 0.0500 0.9812 4.000 0.6324 0.01634 0.00899 -0.0412 0.0480 0.9826 4.250 0.6526 0.01667 0.00933 -0.0397 0.0459 0.9844 4.500 0.6786 0.01695 0.00961 -0.0395 0.0437 0.9848 4.750 0.7025 0.01766 0.01038 -0.0388 0.0417 0.9853 5.000 0.7288 0.01785 0.01061 -0.0387 0.0407 0.9859 5.250 0.7554 0.01812 0.01093 -0.0386 0.0393 0.9866 5.500 0.7823 0.01850 0.01137 -0.0386 0.0378 0.9876 5.750 0.8079 0.01889 0.01179 -0.0384 0.0363 0.9885 6.000 0.8313 0.01939 0.01230 -0.0378 0.0347 0.9892 6.250 0.8545 0.02088 0.01391 -0.0370 0.0329 0.9896 6.500 0.8779 0.02121 0.01433 -0.0363 0.0320 0.9904 6.750 0.9008 0.02168 0.01492 -0.0354 0.0308 0.9912 7.000 0.9230 0.02211 0.01541 -0.0345 0.0294 0.9921 7.250 0.9449 0.02253 0.01588 -0.0335 0.0281 0.9933 7.500 0.9707 0.02346 0.01684 -0.0336 0.0268 0.9948 7.750 0.9939 0.02528 0.01895 -0.0330 0.0256 0.9955 8.000 1.0175 0.02586 0.01972 -0.0324 0.0245 0.9964 8.250 1.0386 0.02656 0.02056 -0.0313 0.0234 0.9971 8.500 1.0597 0.02700 0.02108 -0.0304 0.0224 0.9980 8.750 1.0809 0.02745 0.02157 -0.0296 0.0216 0.9989 9.000 1.1010 0.02911 0.02336 -0.0289 0.0207 1.0000 9.250 1.1066 0.03127 0.02587 -0.0249 0.0201 1.0000 9.500 1.1140 0.03272 0.02762 -0.0212 0.0196 1.0000 9.750 1.1164 0.03476 0.02999 -0.0167 0.0190 1.0000 10.000 1.1172 0.03672 0.03222 -0.0121 0.0184 1.0000 10.250 1.1194 0.03818 0.03388 -0.0079 0.0179 1.0000 10.500 1.1270 0.03877 0.03452 -0.0046 0.0174 1.0000 10.750 1.1339 0.03927 0.03508 -0.0012 0.0171 1.0000 11.000 1.1421 0.03947 0.03529 0.0019 0.0167 1.0000 11.250 1.1427 0.04036 0.03623 0.0062 0.0164 1.0000 11.500 1.1260 0.04248 0.03853 0.0131 0.0162 1.0000 11.750 1.0959 0.04448 0.04073 0.0224 0.0161 1.0000 12.000 1.0654 0.04687 0.04332 0.0308 0.0161 1.0000 12.250 1.0335 0.04976 0.04643 0.0383 0.0160 1.0000 12.500 1.0028 0.05294 0.04981 0.0443 0.0160 1.0000 12.750 0.9729 0.05653 0.05358 0.0489 0.0160 1.0000 13.000 0.9454 0.06056 0.05778 0.0515 0.0161 1.0000 13.250 0.9146 0.06634 0.06375 0.0511 0.0162 1.0000