NACA 64A-010 10.0% (naca64a010-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64A-010 10.0% (naca64a010-il) Reynolds number: 500,000 Max Cl/Cd: 49.94 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64a010-il-500000-n5.txt Download as CSV file: xf-naca64a010-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7039 0.09627 0.09393 -0.0113 1.0000 0.0078
-11.750 -0.8996 0.04915 0.04622 -0.0377 1.0000 0.0070
-11.500 -0.9176 0.04526 0.04214 -0.0370 1.0000 0.0071
-11.250 -0.9369 0.04162 0.03826 -0.0347 1.0000 0.0072
-11.000 -0.9504 0.03885 0.03527 -0.0313 1.0000 0.0073
-10.750 -0.9582 0.03651 0.03271 -0.0276 1.0000 0.0074
-10.500 -0.9623 0.03359 0.02948 -0.0245 1.0000 0.0075
-10.250 -0.9601 0.03106 0.02666 -0.0218 1.0000 0.0077
-10.000 -0.9540 0.02873 0.02403 -0.0194 1.0000 0.0079
-9.750 -0.9440 0.02676 0.02179 -0.0172 1.0000 0.0082
-9.500 -0.9309 0.02515 0.01994 -0.0154 1.0000 0.0085
-9.250 -0.9163 0.02363 0.01820 -0.0136 1.0000 0.0087
-9.000 -0.9002 0.02233 0.01668 -0.0120 1.0000 0.0090
-8.750 -0.8833 0.02117 0.01535 -0.0104 1.0000 0.0091
-8.500 -0.8653 0.02022 0.01425 -0.0089 1.0000 0.0093
-8.250 -0.8505 0.01878 0.01266 -0.0070 1.0000 0.0098
-8.000 -0.8317 0.01813 0.01197 -0.0057 1.0000 0.0102
-7.750 -0.8121 0.01758 0.01137 -0.0044 1.0000 0.0107
-7.500 -0.7923 0.01707 0.01081 -0.0031 1.0000 0.0113
-7.250 -0.7736 0.01640 0.01004 -0.0016 1.0000 0.0117
-7.000 -0.7552 0.01574 0.00931 0.0001 1.0000 0.0122
-6.750 -0.7367 0.01516 0.00865 0.0017 1.0000 0.0127
-6.500 -0.7156 0.01458 0.00800 0.0028 0.9994 0.0130
-6.250 -0.6849 0.01380 0.00715 0.0017 0.9950 0.0137
-6.000 -0.6553 0.01311 0.00641 0.0008 0.9898 0.0146
-5.750 -0.6233 0.01272 0.00601 -0.0004 0.9851 0.0161
-5.500 -0.5930 0.01228 0.00552 -0.0012 0.9788 0.0173
-5.250 -0.5611 0.01187 0.00506 -0.0024 0.9729 0.0184
-5.000 -0.5293 0.01135 0.00448 -0.0035 0.9662 0.0204
-4.750 -0.4975 0.01097 0.00409 -0.0046 0.9579 0.0229
-4.500 -0.4637 0.01067 0.00375 -0.0061 0.9497 0.0258
-4.000 -0.4002 0.00999 0.00309 -0.0082 0.9262 0.0414
-3.750 -0.3707 0.00970 0.00282 -0.0087 0.9120 0.0574
-3.500 -0.3443 0.00932 0.00255 -0.0086 0.8967 0.0925
-3.250 -0.3206 0.00881 0.00226 -0.0080 0.8812 0.1621
-3.000 -0.2997 0.00811 0.00195 -0.0070 0.8661 0.2755
-2.750 -0.2800 0.00738 0.00168 -0.0057 0.8519 0.4057
-2.500 -0.2580 0.00697 0.00156 -0.0047 0.8386 0.4964
-2.250 -0.2343 0.00675 0.00147 -0.0038 0.8265 0.5509
-2.000 -0.2101 0.00658 0.00142 -0.0031 0.8152 0.5965
-1.750 -0.1860 0.00645 0.00139 -0.0022 0.8043 0.6419
-1.500 -0.1607 0.00638 0.00137 -0.0016 0.7933 0.6691
-1.250 -0.1344 0.00634 0.00133 -0.0012 0.7831 0.6861
-1.000 -0.1078 0.00632 0.00130 -0.0009 0.7736 0.6987
-0.750 -0.0810 0.00631 0.00127 -0.0006 0.7636 0.7080
-0.500 -0.0539 0.00631 0.00125 -0.0004 0.7538 0.7172
-0.250 -0.0270 0.00630 0.00123 -0.0002 0.7448 0.7261
0.000 0.0000 0.00630 0.00123 0.0000 0.7354 0.7354
0.250 0.0270 0.00630 0.00123 0.0002 0.7261 0.7448
0.500 0.0539 0.00631 0.00125 0.0004 0.7172 0.7538
0.750 0.0810 0.00631 0.00127 0.0006 0.7080 0.7636
1.000 0.1079 0.00632 0.00130 0.0009 0.6987 0.7737
1.250 0.1344 0.00634 0.00133 0.0012 0.6862 0.7831
1.500 0.1608 0.00638 0.00137 0.0016 0.6691 0.7933
1.750 0.1861 0.00645 0.00139 0.0022 0.6418 0.8042
2.000 0.2101 0.00658 0.00142 0.0031 0.5965 0.8152
2.250 0.2342 0.00675 0.00147 0.0038 0.5504 0.8264
2.500 0.2580 0.00698 0.00155 0.0047 0.4954 0.8386
2.750 0.2800 0.00739 0.00168 0.0057 0.4043 0.8519
3.000 0.2998 0.00809 0.00195 0.0070 0.2781 0.8660
3.250 0.3206 0.00880 0.00226 0.0080 0.1630 0.8812
3.500 0.3443 0.00931 0.00255 0.0086 0.0936 0.8967
3.750 0.3708 0.00970 0.00282 0.0086 0.0581 0.9121
4.000 0.4002 0.00999 0.00309 0.0081 0.0415 0.9264
4.250 0.4315 0.01030 0.00339 0.0072 0.0325 0.9388
4.500 0.4637 0.01067 0.00375 0.0061 0.0259 0.9497
4.750 0.4975 0.01097 0.00409 0.0046 0.0229 0.9578
5.000 0.5293 0.01135 0.00448 0.0035 0.0203 0.9661
5.250 0.5612 0.01186 0.00504 0.0024 0.0183 0.9728
5.500 0.5930 0.01228 0.00552 0.0012 0.0173 0.9788
5.750 0.6234 0.01270 0.00598 0.0004 0.0159 0.9851
6.000 0.6552 0.01312 0.00643 -0.0008 0.0147 0.9898
6.250 0.6848 0.01381 0.00716 -0.0016 0.0136 0.9951
6.500 0.7155 0.01458 0.00800 -0.0027 0.0130 0.9994
6.750 0.7370 0.01513 0.00863 -0.0017 0.0126 1.0000
7.000 0.7552 0.01575 0.00932 -0.0001 0.0121 1.0000
7.250 0.7737 0.01640 0.01004 0.0016 0.0117 1.0000
7.500 0.7924 0.01707 0.01081 0.0031 0.0112 1.0000
7.750 0.8118 0.01765 0.01145 0.0044 0.0107 1.0000
8.000 0.8313 0.01821 0.01206 0.0057 0.0103 1.0000
8.250 0.8502 0.01883 0.01273 0.0070 0.0098 1.0000
8.500 0.8649 0.02029 0.01431 0.0090 0.0093 1.0000
8.750 0.8831 0.02120 0.01537 0.0104 0.0092 1.0000
9.000 0.9002 0.02232 0.01667 0.0120 0.0090 1.0000
9.250 0.9165 0.02358 0.01814 0.0136 0.0087 1.0000
9.500 0.9308 0.02515 0.01994 0.0154 0.0084 1.0000
9.750 0.9433 0.02689 0.02193 0.0173 0.0083 1.0000
10.000 0.9531 0.02888 0.02420 0.0195 0.0080 1.0000
10.250 0.9603 0.03102 0.02661 0.0218 0.0077 1.0000
10.500 0.9621 0.03362 0.02952 0.0245 0.0076 1.0000
10.750 0.9616 0.03605 0.03221 0.0273 0.0073 1.0000
11.000 0.9494 0.03897 0.03540 0.0314 0.0073 1.0000
11.250 0.9297 0.04244 0.03914 0.0351 0.0072 1.0000
11.500 0.9203 0.04497 0.04183 0.0369 0.0071 1.0000
11.750 0.8692 0.05324 0.05047 0.0369 0.0071 1.0000
12.000 0.7061 0.09595 0.09361 0.0114 0.0078 1.0000
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Polar data table (+)
Polar graphs
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