NACA 0010-64 (naca001064-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0010-64 (naca001064-il) Reynolds number: 50,000 Max Cl/Cd: 25.83 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001064-il-50000.txt Download as CSV file: xf-naca001064-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-64
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5822 0.10163 0.09421 0.0153 1.0000 0.4129
-8.500 -0.5567 0.09678 0.08929 0.0155 1.0000 0.4240
-8.250 -0.7479 0.07124 0.06380 -0.0183 1.0000 0.1871
-8.000 -0.7457 0.06458 0.05690 -0.0184 1.0000 0.1668
-7.750 -0.7599 0.05899 0.05073 -0.0167 1.0000 0.1548
-7.500 -0.7546 0.05495 0.04646 -0.0149 1.0000 0.1529
-7.250 -0.7494 0.05118 0.04235 -0.0127 1.0000 0.1515
-7.000 -0.7423 0.04753 0.03828 -0.0104 1.0000 0.1496
-6.750 -0.7332 0.04402 0.03426 -0.0079 1.0000 0.1472
-6.500 -0.7199 0.04095 0.03070 -0.0057 1.0000 0.1466
-6.250 -0.7037 0.03852 0.02794 -0.0038 1.0000 0.1502
-6.000 -0.6864 0.03622 0.02519 -0.0018 1.0000 0.1541
-5.750 -0.6665 0.03403 0.02247 0.0000 1.0000 0.1568
-5.500 -0.6421 0.03169 0.02012 0.0008 1.0000 0.1617
-5.250 -0.6191 0.03005 0.01813 0.0021 1.0000 0.1707
-5.000 -0.5933 0.02828 0.01640 0.0028 1.0000 0.1829
-4.750 -0.5638 0.02653 0.01465 0.0032 1.0000 0.1983
-4.500 -0.5349 0.02484 0.01316 0.0035 1.0000 0.2280
-4.250 -0.5102 0.02274 0.01155 0.0045 1.0000 0.2905
-4.000 -0.5062 0.01953 0.01148 0.0125 1.0000 0.6875
-3.750 -0.2090 0.02554 0.01563 -0.0198 1.0000 0.9782
-3.500 -0.1432 0.02418 0.01388 -0.0291 1.0000 1.0000
-3.250 -0.1291 0.02348 0.01307 -0.0284 1.0000 1.0000
-3.000 -0.1151 0.02288 0.01233 -0.0276 1.0000 1.0000
-2.750 -0.1013 0.02234 0.01171 -0.0265 1.0000 1.0000
-2.500 -0.0880 0.02188 0.01117 -0.0252 1.0000 1.0000
-2.250 -0.0753 0.02147 0.01070 -0.0237 1.0000 1.0000
-2.000 -0.0635 0.02113 0.01030 -0.0219 1.0000 1.0000
-1.750 -0.0527 0.02083 0.00996 -0.0199 1.0000 1.0000
-1.500 -0.0428 0.02059 0.00969 -0.0176 1.0000 1.0000
-1.250 -0.0338 0.02038 0.00947 -0.0151 1.0000 1.0000
-1.000 -0.0256 0.02022 0.00929 -0.0124 1.0000 1.0000
-0.750 -0.0183 0.02010 0.00917 -0.0095 1.0000 1.0000
-0.500 -0.0117 0.02002 0.00907 -0.0064 1.0000 1.0000
-0.250 -0.0057 0.01997 0.00902 -0.0032 1.0000 1.0000
0.000 0.0000 0.01995 0.00900 0.0000 1.0000 1.0000
0.250 0.0057 0.01997 0.00902 0.0032 1.0000 1.0000
0.500 0.0117 0.02002 0.00907 0.0064 1.0000 1.0000
0.750 0.0183 0.02010 0.00916 0.0095 1.0000 1.0000
1.000 0.0256 0.02022 0.00929 0.0124 1.0000 1.0000
1.250 0.0338 0.02038 0.00946 0.0151 1.0000 1.0000
1.500 0.0428 0.02058 0.00968 0.0176 1.0000 1.0000
1.750 0.0527 0.02083 0.00996 0.0198 1.0000 1.0000
2.000 0.0635 0.02112 0.01030 0.0219 1.0000 1.0000
2.250 0.0754 0.02147 0.01069 0.0237 1.0000 1.0000
2.500 0.0881 0.02187 0.01116 0.0252 1.0000 1.0000
2.750 0.1014 0.02233 0.01170 0.0265 1.0000 1.0000
3.000 0.1152 0.02287 0.01232 0.0275 1.0000 1.0000
3.250 0.1293 0.02347 0.01305 0.0284 1.0000 1.0000
3.500 0.1434 0.02417 0.01387 0.0291 1.0000 1.0000
3.750 0.2090 0.02553 0.01561 0.0198 0.9782 1.0000
4.000 0.5055 0.01957 0.01155 -0.0126 0.6955 1.0000
4.250 0.5102 0.02273 0.01155 -0.0045 0.2906 1.0000
4.500 0.5348 0.02484 0.01315 -0.0035 0.2280 1.0000
4.750 0.5638 0.02653 0.01465 -0.0032 0.1983 1.0000
5.000 0.5932 0.02827 0.01640 -0.0028 0.1829 1.0000
5.250 0.6190 0.03005 0.01813 -0.0021 0.1707 1.0000
5.500 0.6421 0.03169 0.02012 -0.0008 0.1617 1.0000
5.750 0.6664 0.03403 0.02247 0.0000 0.1568 1.0000
6.000 0.6864 0.03622 0.02518 0.0018 0.1541 1.0000
6.250 0.7036 0.03852 0.02794 0.0038 0.1502 1.0000
6.500 0.7198 0.04095 0.03070 0.0057 0.1466 1.0000
6.750 0.7331 0.04402 0.03426 0.0079 0.1472 1.0000
7.000 0.7423 0.04753 0.03828 0.0104 0.1496 1.0000
7.250 0.7493 0.05118 0.04234 0.0127 0.1515 1.0000
7.500 0.7545 0.05495 0.04645 0.0149 0.1529 1.0000
7.750 0.7599 0.05899 0.05073 0.0167 0.1548 1.0000
8.000 0.7457 0.06459 0.05690 0.0184 0.1668 1.0000
8.250 0.6524 0.06116 0.05424 0.0235 0.1835 1.0000
8.500 0.5636 0.09726 0.08979 -0.0159 0.4260 1.0000
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Polar data table (+)
Polar graphs
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