NACA 63A210 (naca63a210-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63A210 (naca63a210-il) Reynolds number: 50,000 Max Cl/Cd: 28.28 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca63a210-il-50000.txt Download as CSV file: xf-naca63a210-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63A210
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5058 0.09678 0.09183 0.0199 1.0000 0.3846
-7.750 -0.4937 0.09337 0.08846 0.0211 1.0000 0.4121
-6.250 -0.5511 0.05418 0.04876 -0.0292 1.0000 0.1817
-6.000 -0.5221 0.04751 0.04121 -0.0333 0.9665 0.1355
-5.750 -0.4915 0.04262 0.03553 -0.0354 0.9438 0.1156
-5.500 -0.4602 0.03921 0.03133 -0.0366 0.9293 0.1079
-5.250 -0.4294 0.03597 0.02757 -0.0375 0.9194 0.1061
-5.000 -0.3973 0.03306 0.02415 -0.0381 0.9118 0.1034
-4.750 -0.3629 0.03050 0.02103 -0.0385 0.9063 0.1005
-4.500 -0.3287 0.02830 0.01851 -0.0388 0.9013 0.1009
-4.250 -0.2936 0.02639 0.01645 -0.0391 0.8975 0.1056
-4.000 -0.2615 0.02475 0.01470 -0.0392 0.8941 0.1200
-3.750 -0.2340 0.02327 0.01317 -0.0388 0.8904 0.1365
-3.500 -0.0836 0.02229 0.01487 -0.0360 0.9090 0.9856
-3.250 -0.0335 0.02131 0.01333 -0.0429 0.9039 1.0000
-3.000 -0.0099 0.02082 0.01253 -0.0447 0.8972 1.0000
-2.750 0.0138 0.02042 0.01184 -0.0463 0.8922 1.0000
-2.500 0.0373 0.02010 0.01128 -0.0479 0.8879 1.0000
-2.250 0.0608 0.01985 0.01082 -0.0493 0.8844 1.0000
-2.000 0.0842 0.01968 0.01041 -0.0507 0.8812 1.0000
-1.750 0.1077 0.01957 0.01012 -0.0519 0.8787 1.0000
-1.500 0.1305 0.01955 0.00996 -0.0531 0.8765 1.0000
-1.250 0.1525 0.01960 0.00990 -0.0542 0.8747 1.0000
-1.000 0.1736 0.01974 0.00991 -0.0550 0.8729 1.0000
-0.750 0.1932 0.01995 0.01003 -0.0555 0.8712 1.0000
-0.500 0.2109 0.02026 0.01026 -0.0557 0.8698 1.0000
-0.250 0.2266 0.02065 0.01058 -0.0555 0.8686 1.0000
0.000 0.2403 0.02113 0.01100 -0.0549 0.8675 1.0000
0.250 0.2533 0.02167 0.01148 -0.0540 0.8662 1.0000
0.500 0.2680 0.02225 0.01200 -0.0533 0.8648 1.0000
0.750 0.2813 0.02293 0.01260 -0.0525 0.8639 1.0000
1.000 0.2889 0.02375 0.01336 -0.0507 0.8630 1.0000
1.250 0.2961 0.02460 0.01414 -0.0488 0.8612 1.0000
1.500 0.3064 0.02542 0.01491 -0.0473 0.8583 1.0000
1.750 0.3220 0.02621 0.01568 -0.0466 0.8552 1.0000
2.000 0.3405 0.02703 0.01650 -0.0464 0.8527 1.0000
2.250 0.3643 0.02784 0.01737 -0.0469 0.8501 1.0000
2.500 0.3766 0.02884 0.01837 -0.0459 0.8477 1.0000
2.750 0.3843 0.02991 0.01944 -0.0443 0.8456 1.0000
3.000 0.3963 0.03095 0.02051 -0.0432 0.8425 1.0000
3.250 0.4241 0.03186 0.02153 -0.0444 0.8367 1.0000
3.500 0.4394 0.03291 0.02265 -0.0437 0.8300 1.0000
3.750 0.4788 0.03373 0.02373 -0.0461 0.8200 1.0000
4.000 0.4855 0.03493 0.02501 -0.0442 0.8112 1.0000
4.250 0.5120 0.03592 0.02618 -0.0446 0.7983 1.0000
4.500 0.5479 0.03666 0.02718 -0.0458 0.7806 1.0000
4.750 0.5873 0.03709 0.02798 -0.0462 0.7581 1.0000
5.000 0.6290 0.03689 0.02813 -0.0451 0.7294 1.0000
5.250 0.6630 0.03649 0.02805 -0.0420 0.6974 1.0000
5.500 0.7033 0.03495 0.02692 -0.0368 0.6611 1.0000
5.750 0.7269 0.03447 0.02669 -0.0313 0.6240 1.0000
6.000 0.7481 0.03397 0.02641 -0.0252 0.5824 1.0000
6.250 0.7715 0.03382 0.02623 -0.0176 0.5318 1.0000
6.500 0.7773 0.03123 0.02436 -0.0128 0.4338 1.0000
6.750 0.7979 0.02821 0.01978 -0.0054 0.2773 1.0000
7.000 0.8048 0.03045 0.02140 -0.0023 0.2214 1.0000
7.250 0.8150 0.03264 0.02329 0.0003 0.1787 1.0000
7.500 0.8339 0.03509 0.02553 0.0028 0.1473 1.0000
7.750 0.8567 0.03771 0.02804 0.0044 0.1223 1.0000
8.000 0.8831 0.04126 0.03171 0.0057 0.1104 1.0000
8.250 0.9038 0.04469 0.03517 0.0066 0.0984 1.0000
8.500 0.9173 0.04832 0.03953 0.0083 0.0940 1.0000
8.750 0.9282 0.05267 0.04440 0.0097 0.0927 1.0000
9.000 0.9334 0.05725 0.04947 0.0108 0.0924 1.0000
9.250 0.9329 0.06189 0.05455 0.0116 0.0923 1.0000
9.500 0.9259 0.06673 0.05975 0.0119 0.0929 1.0000
9.750 0.9140 0.07173 0.06504 0.0116 0.0941 1.0000
10.000 0.8994 0.07678 0.07026 0.0109 0.0956 1.0000
10.250 0.8852 0.08200 0.07557 0.0095 0.0970 1.0000
10.500 0.8754 0.08767 0.08128 0.0076 0.0981 1.0000
10.750 0.8729 0.09364 0.08726 0.0061 0.0989 1.0000
11.000 0.8269 0.10478 0.09847 -0.0045 0.1128 1.0000
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Polar data table (+)
Polar graphs
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