NACA 64-209 (naca64209-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64-209 (naca64209-il) Reynolds number: 50,000 Max Cl/Cd: 31.5 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64209-il-50000.txt Download as CSV file: xf-naca64209-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-209
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5191 0.10901 0.10199 0.0026 1.0000 0.2931
-9.000 -0.5123 0.10587 0.09888 0.0032 1.0000 0.3133
-8.750 -0.5228 0.10413 0.09724 0.0029 1.0000 0.3311
-8.500 -0.5017 0.09987 0.09296 0.0048 1.0000 0.3578
-8.250 -0.4859 0.09596 0.08905 0.0060 1.0000 0.3815
-7.750 -0.4712 0.08991 0.08307 0.0079 1.0000 0.4272
-7.500 -0.4620 0.08647 0.07967 0.0088 1.0000 0.4484
-7.250 -0.4684 0.08490 0.07819 0.0105 1.0000 0.4730
-7.000 -0.4396 0.07980 0.07305 0.0107 1.0000 0.4938
-6.750 -0.4344 0.07662 0.06988 0.0111 1.0000 0.5068
-6.500 -0.5033 0.04815 0.04220 -0.0265 1.0000 0.2367
-6.250 -0.5537 0.05081 0.04305 -0.0372 1.0000 0.1608
-6.000 -0.5362 0.04603 0.03779 -0.0373 1.0000 0.1459
-5.750 -0.5181 0.04175 0.03314 -0.0368 1.0000 0.1372
-5.500 -0.4977 0.03827 0.02901 -0.0360 1.0000 0.1297
-5.250 -0.4768 0.03506 0.02535 -0.0351 1.0000 0.1271
-5.000 -0.4550 0.03260 0.02232 -0.0340 1.0000 0.1313
-4.750 -0.4343 0.03025 0.01987 -0.0329 1.0000 0.1418
-4.500 -0.4105 0.02827 0.01739 -0.0316 1.0000 0.1461
-4.250 -0.3882 0.02637 0.01549 -0.0304 1.0000 0.1545
-4.000 -0.3645 0.02496 0.01383 -0.0289 1.0000 0.1585
-3.750 -0.3414 0.02379 0.01252 -0.0272 1.0000 0.1617
-3.500 -0.3206 0.02269 0.01147 -0.0255 1.0000 0.1667
-3.250 -0.3000 0.02184 0.01053 -0.0239 1.0000 0.1739
-3.000 -0.2808 0.02093 0.00966 -0.0225 1.0000 0.1850
-2.750 -0.2610 0.01995 0.00878 -0.0215 1.0000 0.2061
-2.500 -0.2497 0.01737 0.00843 -0.0191 1.0000 0.5522
-2.250 -0.2547 0.01745 0.00920 -0.0092 1.0000 0.7659
-2.000 -0.0472 0.01850 0.00915 -0.0294 1.0000 1.0000
-1.750 -0.0529 0.01832 0.00896 -0.0256 1.0000 1.0000
-1.500 -0.0637 0.01817 0.00879 -0.0210 1.0000 1.0000
-1.250 -0.0775 0.01799 0.00860 -0.0161 1.0000 1.0000
-1.000 -0.0903 0.01778 0.00836 -0.0114 1.0000 1.0000
-0.750 -0.0952 0.01764 0.00812 -0.0078 1.0000 1.0000
-0.500 -0.0866 0.01765 0.00797 -0.0063 1.0000 1.0000
-0.250 -0.0714 0.01778 0.00792 -0.0058 1.0000 1.0000
0.000 -0.0533 0.01800 0.00797 -0.0057 1.0000 1.0000
0.250 -0.0341 0.01828 0.00811 -0.0057 1.0000 1.0000
0.500 -0.0143 0.01862 0.00832 -0.0058 1.0000 1.0000
0.750 0.0056 0.01900 0.00860 -0.0060 1.0000 1.0000
1.000 0.0256 0.01943 0.00893 -0.0061 1.0000 1.0000
1.250 0.0456 0.01990 0.00933 -0.0063 1.0000 1.0000
1.500 0.0655 0.02041 0.00979 -0.0065 1.0000 1.0000
1.750 0.0853 0.02096 0.01031 -0.0066 1.0000 1.0000
2.000 0.1050 0.02155 0.01089 -0.0068 1.0000 1.0000
2.250 0.1245 0.02218 0.01152 -0.0071 1.0000 1.0000
2.500 0.1438 0.02286 0.01221 -0.0073 1.0000 1.0000
2.750 0.1798 0.02393 0.01336 -0.0108 0.9916 1.0000
3.000 0.2223 0.02518 0.01475 -0.0154 0.9794 1.0000
3.250 0.2641 0.02640 0.01612 -0.0197 0.9665 1.0000
3.500 0.3049 0.02760 0.01749 -0.0237 0.9527 1.0000
3.750 0.3442 0.02874 0.01886 -0.0273 0.9374 1.0000
4.000 0.3844 0.02985 0.02026 -0.0308 0.9196 1.0000
4.250 0.4380 0.03097 0.02177 -0.0360 0.8978 1.0000
4.500 0.4899 0.03150 0.02277 -0.0396 0.8648 1.0000
4.750 0.6269 0.01990 0.01065 -0.0236 0.3379 1.0000
5.000 0.6291 0.02366 0.01273 -0.0201 0.1954 1.0000
5.250 0.6493 0.02580 0.01458 -0.0187 0.1589 1.0000
5.500 0.6806 0.02785 0.01656 -0.0180 0.1404 1.0000
5.750 0.7125 0.03000 0.01865 -0.0178 0.1251 1.0000
6.000 0.7457 0.03273 0.02147 -0.0177 0.1190 1.0000
6.250 0.7749 0.03543 0.02461 -0.0170 0.1165 1.0000
6.500 0.8003 0.03822 0.02785 -0.0162 0.1128 1.0000
6.750 0.8247 0.04156 0.03126 -0.0158 0.1084 1.0000
7.000 0.8437 0.04481 0.03534 -0.0142 0.1109 1.0000
7.250 0.8595 0.04899 0.04020 -0.0128 0.1157 1.0000
7.500 0.8770 0.05371 0.04520 -0.0122 0.1201 1.0000
7.750 0.8815 0.05852 0.05089 -0.0109 0.1312 1.0000
8.000 0.8837 0.06426 0.05721 -0.0106 0.1453 1.0000
8.250 0.8713 0.07107 0.06459 -0.0120 0.1674 1.0000
8.500 0.7822 0.06783 0.06192 -0.0079 0.1659 1.0000
8.750 0.7523 0.07454 0.06868 -0.0093 0.1743 1.0000
9.000 0.7040 0.08280 0.07691 -0.0150 0.1807 1.0000
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Polar data table (+)
Polar graphs
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