NACA 64A-010 10.0% (naca64a010-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64A-010 10.0% (naca64a010-il) Reynolds number: 500,000 Max Cl/Cd: 50.79 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64a010-il-500000.txt Download as CSV file: xf-naca64a010-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64A-010 10.0%
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.8014 0.02966 0.02488 -0.0120 1.0000 0.0171
-7.750 -0.7918 0.02643 0.02126 -0.0091 1.0000 0.0169
-7.500 -0.7774 0.02405 0.01859 -0.0069 1.0000 0.0171
-7.250 -0.7610 0.02199 0.01627 -0.0049 1.0000 0.0173
-7.000 -0.7422 0.02080 0.01489 -0.0032 1.0000 0.0179
-6.750 -0.7223 0.02047 0.01444 -0.0017 1.0000 0.0186
-6.500 -0.7052 0.01804 0.01179 0.0002 1.0000 0.0192
-6.250 -0.6885 0.01635 0.01002 0.0022 1.0000 0.0200
-6.000 -0.6715 0.01545 0.00907 0.0041 1.0000 0.0206
-5.750 -0.6545 0.01483 0.00843 0.0060 1.0000 0.0217
-5.500 -0.6384 0.01422 0.00778 0.0081 1.0000 0.0225
-5.250 -0.6174 0.01368 0.00719 0.0092 0.9993 0.0240
-5.000 -0.5806 0.01322 0.00669 0.0071 0.9961 0.0257
-4.750 -0.5488 0.01200 0.00537 0.0058 0.9917 0.0282
-4.500 -0.5133 0.01143 0.00479 0.0038 0.9877 0.0315
-4.250 -0.4781 0.01100 0.00431 0.0020 0.9832 0.0361
-4.000 -0.4433 0.01045 0.00375 0.0003 0.9784 0.0462
-3.750 -0.4101 0.00968 0.00321 -0.0012 0.9734 0.0917
-3.500 -0.3821 0.00827 0.00266 -0.0024 0.9668 0.2857
-3.250 -0.3581 0.00704 0.00232 -0.0024 0.9576 0.5037
-3.000 -0.3252 0.00668 0.00218 -0.0035 0.9512 0.5758
-2.750 -0.2961 0.00650 0.00208 -0.0038 0.9401 0.6145
-2.500 -0.2663 0.00636 0.00199 -0.0041 0.9292 0.6432
-2.250 -0.2378 0.00626 0.00192 -0.0041 0.9176 0.6700
-2.000 -0.2106 0.00619 0.00187 -0.0037 0.9055 0.6956
-1.750 -0.1848 0.00614 0.00186 -0.0030 0.8929 0.7233
-1.500 -0.1590 0.00612 0.00184 -0.0024 0.8800 0.7426
-1.250 -0.1328 0.00610 0.00181 -0.0019 0.8675 0.7568
-1.000 -0.1064 0.00608 0.00177 -0.0014 0.8555 0.7689
-0.750 -0.0798 0.00607 0.00174 -0.0011 0.8438 0.7796
-0.500 -0.0532 0.00608 0.00171 -0.0007 0.8327 0.7903
-0.250 -0.0265 0.00607 0.00169 -0.0004 0.8219 0.8001
0.000 0.0000 0.00606 0.00169 0.0000 0.8107 0.8107
0.250 0.0266 0.00607 0.00169 0.0004 0.8001 0.8219
0.500 0.0532 0.00608 0.00171 0.0007 0.7903 0.8328
0.750 0.0799 0.00607 0.00174 0.0011 0.7796 0.8438
1.000 0.1065 0.00608 0.00177 0.0014 0.7689 0.8555
1.250 0.1328 0.00610 0.00181 0.0019 0.7568 0.8675
1.500 0.1590 0.00612 0.00184 0.0024 0.7426 0.8800
1.750 0.1848 0.00614 0.00186 0.0030 0.7232 0.8928
2.000 0.2106 0.00619 0.00187 0.0037 0.6957 0.9054
2.250 0.2378 0.00626 0.00192 0.0041 0.6698 0.9176
2.500 0.2663 0.00636 0.00199 0.0041 0.6430 0.9292
2.750 0.2961 0.00650 0.00208 0.0038 0.6146 0.9402
3.000 0.3253 0.00668 0.00218 0.0035 0.5769 0.9511
3.250 0.3581 0.00705 0.00232 0.0024 0.5034 0.9576
3.500 0.3823 0.00824 0.00266 0.0023 0.2911 0.9667
3.750 0.4101 0.00968 0.00322 0.0012 0.0917 0.9734
4.000 0.4433 0.01045 0.00375 -0.0003 0.0463 0.9784
4.250 0.4779 0.01104 0.00436 -0.0020 0.0355 0.9833
4.500 0.5132 0.01144 0.00480 -0.0038 0.0317 0.9877
4.750 0.5487 0.01202 0.00539 -0.0057 0.0280 0.9916
5.000 0.5808 0.01319 0.00666 -0.0071 0.0256 0.9961
5.250 0.6174 0.01367 0.00719 -0.0092 0.0239 0.9993
5.500 0.6386 0.01420 0.00775 -0.0082 0.0225 1.0000
5.750 0.6547 0.01480 0.00839 -0.0061 0.0215 1.0000
6.000 0.6715 0.01548 0.00910 -0.0041 0.0207 1.0000
6.250 0.6885 0.01637 0.01003 -0.0021 0.0199 1.0000
6.500 0.7053 0.01800 0.01175 -0.0002 0.0192 1.0000
6.750 0.7223 0.02048 0.01445 0.0017 0.0186 1.0000
7.000 0.7419 0.02102 0.01513 0.0033 0.0180 1.0000
7.250 0.7608 0.02209 0.01637 0.0049 0.0173 1.0000
7.500 0.7773 0.02413 0.01867 0.0069 0.0171 1.0000
7.750 0.7917 0.02646 0.02130 0.0091 0.0170 1.0000
8.000 0.8011 0.02971 0.02494 0.0120 0.0172 1.0000
8.250 0.8038 0.03390 0.02953 0.0154 0.0178 1.0000
14.500 0.5143 0.14813 0.14595 -0.0098 0.0186 1.0000
14.750 0.5160 0.15146 0.14928 -0.0119 0.0185 1.0000
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Polar data table (+)
Polar graphs
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