NACA 64A410 (naca64a410-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64A410 (naca64a410-il) Reynolds number: 200,000 Max Cl/Cd: 71.27 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64a410-il-200000-n5.txt Download as CSV file: xf-naca64a410-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64A410
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4310 0.08885 0.08529 -0.0422 1.0000 0.0181
-9.000 -0.4346 0.08478 0.08128 -0.0438 1.0000 0.0177
-8.750 -0.4430 0.08090 0.07747 -0.0446 1.0000 0.0172
-8.500 -0.4590 0.07771 0.07437 -0.0440 1.0000 0.0169
-8.250 -0.4786 0.07441 0.07116 -0.0438 0.9985 0.0167
-8.000 -0.4781 0.05505 0.05145 -0.0671 0.9864 0.0149
-7.750 -0.4687 0.04632 0.04229 -0.0729 0.9792 0.0147
-7.500 -0.4524 0.04008 0.03560 -0.0769 0.9745 0.0148
-7.250 -0.4342 0.03590 0.03102 -0.0787 0.9688 0.0151
-7.000 -0.4087 0.03245 0.02718 -0.0810 0.9655 0.0156
-6.750 -0.3837 0.03011 0.02451 -0.0821 0.9614 0.0164
-6.500 -0.3588 0.02787 0.02189 -0.0828 0.9564 0.0179
-6.250 -0.3305 0.02494 0.01840 -0.0837 0.9529 0.0190
-6.000 -0.3000 0.02264 0.01560 -0.0847 0.9502 0.0197
-5.750 -0.2767 0.02092 0.01355 -0.0841 0.9442 0.0204
-5.500 -0.2483 0.01969 0.01221 -0.0848 0.9403 0.0219
-5.250 -0.2173 0.01888 0.01127 -0.0857 0.9373 0.0239
-5.000 -0.1907 0.01785 0.01009 -0.0855 0.9325 0.0251
-4.750 -0.1638 0.01692 0.00904 -0.0854 0.9274 0.0263
-4.500 -0.1342 0.01619 0.00817 -0.0858 0.9237 0.0277
-4.250 -0.1080 0.01532 0.00732 -0.0858 0.9189 0.0304
-4.000 -0.0822 0.01476 0.00672 -0.0855 0.9130 0.0328
-3.750 -0.0535 0.01418 0.00607 -0.0857 0.9088 0.0355
-3.500 -0.0274 0.01369 0.00549 -0.0854 0.9031 0.0387
-3.250 -0.0009 0.01322 0.00498 -0.0853 0.8973 0.0455
-3.000 0.0278 0.01275 0.00445 -0.0855 0.8931 0.0551
-2.750 0.0527 0.01231 0.00420 -0.0852 0.8862 0.0937
-2.500 0.0804 0.01196 0.00389 -0.0852 0.8804 0.1327
-2.250 0.1055 0.01134 0.00363 -0.0850 0.8730 0.2309
-2.000 0.1287 0.01038 0.00347 -0.0846 0.8655 0.4609
-1.750 0.1530 0.01007 0.00346 -0.0837 0.8567 0.5625
-1.500 0.1793 0.00988 0.00338 -0.0831 0.8494 0.6192
-1.250 0.2040 0.00979 0.00338 -0.0823 0.8400 0.6632
-1.000 0.2308 0.00970 0.00331 -0.0818 0.8333 0.6933
-0.750 0.2566 0.00965 0.00328 -0.0813 0.8238 0.7157
-0.500 0.2832 0.00958 0.00320 -0.0808 0.8144 0.7325
-0.250 0.3102 0.00950 0.00310 -0.0804 0.8051 0.7483
0.000 0.3367 0.00946 0.00306 -0.0801 0.7950 0.7625
0.250 0.3637 0.00942 0.00301 -0.0798 0.7860 0.7764
0.500 0.3909 0.00936 0.00295 -0.0795 0.7772 0.7911
0.750 0.4175 0.00931 0.00294 -0.0791 0.7674 0.8071
1.000 0.4441 0.00926 0.00293 -0.0786 0.7582 0.8274
1.250 0.4712 0.00918 0.00292 -0.0782 0.7489 0.8588
1.500 0.5048 0.00910 0.00295 -0.0792 0.7383 0.9163
1.750 0.5450 0.00909 0.00294 -0.0818 0.7256 1.0000
2.000 0.5718 0.00918 0.00299 -0.0817 0.7145 1.0000
2.250 0.5986 0.00929 0.00306 -0.0815 0.7032 1.0000
2.500 0.6250 0.00941 0.00316 -0.0812 0.6906 1.0000
2.750 0.6508 0.00954 0.00326 -0.0808 0.6723 1.0000
3.000 0.6757 0.00970 0.00335 -0.0802 0.6476 1.0000
3.500 0.7234 0.01015 0.00356 -0.0785 0.5821 1.0000
3.750 0.7455 0.01049 0.00374 -0.0773 0.5356 1.0000
4.000 0.7656 0.01099 0.00395 -0.0759 0.4721 1.0000
4.250 0.7809 0.01187 0.00432 -0.0738 0.3662 1.0000
4.500 0.7936 0.01314 0.00496 -0.0716 0.2445 1.0000
5.000 0.8290 0.01501 0.00619 -0.0689 0.1228 1.0000
5.250 0.8504 0.01560 0.00672 -0.0681 0.1003 1.0000
5.500 0.8698 0.01638 0.00723 -0.0669 0.0548 1.0000
5.750 0.8897 0.01712 0.00797 -0.0658 0.0434 1.0000
6.000 0.9099 0.01782 0.00875 -0.0646 0.0370 1.0000
6.250 0.9299 0.01853 0.00953 -0.0635 0.0322 1.0000
6.500 0.9477 0.01945 0.01050 -0.0620 0.0290 1.0000
6.750 0.9668 0.02022 0.01137 -0.0607 0.0271 1.0000
7.000 0.9855 0.02101 0.01224 -0.0593 0.0251 1.0000
7.250 1.0040 0.02180 0.01309 -0.0581 0.0232 1.0000
7.500 1.0191 0.02294 0.01425 -0.0564 0.0217 1.0000
7.750 1.0352 0.02409 0.01547 -0.0547 0.0210 1.0000
8.000 1.0527 0.02519 0.01667 -0.0533 0.0204 1.0000
8.250 1.0706 0.02639 0.01799 -0.0519 0.0197 1.0000
8.500 1.0896 0.02773 0.01946 -0.0507 0.0191 1.0000
8.750 1.1099 0.02920 0.02106 -0.0497 0.0185 1.0000
9.000 1.1299 0.03069 0.02271 -0.0488 0.0179 1.0000
9.250 1.1475 0.03197 0.02412 -0.0476 0.0171 1.0000
9.500 1.1629 0.03317 0.02542 -0.0462 0.0163 1.0000
9.750 1.1782 0.03484 0.02720 -0.0449 0.0157 1.0000
10.000 1.1941 0.03781 0.03041 -0.0439 0.0152 1.0000
10.250 1.2046 0.03987 0.03281 -0.0418 0.0150 1.0000
10.500 1.2114 0.04222 0.03550 -0.0394 0.0147 1.0000
10.750 1.2137 0.04482 0.03844 -0.0366 0.0145 1.0000
11.000 1.2115 0.04752 0.04149 -0.0335 0.0141 1.0000
11.250 1.2059 0.05037 0.04466 -0.0306 0.0137 1.0000
11.500 1.1976 0.05339 0.04799 -0.0279 0.0134 1.0000
11.750 1.1874 0.05662 0.05149 -0.0256 0.0130 1.0000
12.000 1.1750 0.06017 0.05528 -0.0239 0.0128 1.0000
12.250 1.1598 0.06426 0.05963 -0.0227 0.0126 1.0000
12.500 1.1418 0.06896 0.06457 -0.0223 0.0125 1.0000
12.750 1.1210 0.07445 0.07030 -0.0230 0.0125 1.0000
13.000 1.0978 0.08083 0.07690 -0.0248 0.0125 1.0000
13.250 1.0720 0.08837 0.08465 -0.0280 0.0126 1.0000
13.500 1.0435 0.09750 0.09398 -0.0331 0.0128 1.0000
13.750 1.0101 0.10971 0.10638 -0.0410 0.0132 1.0000
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Polar data table (+)
Polar graphs
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