NACA 0010-64 (naca001064-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-64 (naca001064-il) Reynolds number: 50,000 Max Cl/Cd: 25.17 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001064-il-50000-n5.txt Download as CSV file: xf-naca001064-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6931 0.09210 0.08460 -0.0246 1.0000 0.0631
-10.500 -0.7120 0.08500 0.07750 -0.0291 1.0000 0.0625
-10.250 -0.7341 0.07902 0.07146 -0.0316 1.0000 0.0620
-10.000 -0.7570 0.07415 0.06650 -0.0318 1.0000 0.0616
-9.750 -0.7776 0.06990 0.06214 -0.0304 1.0000 0.0615
-9.500 -0.7925 0.06566 0.05768 -0.0287 1.0000 0.0615
-9.250 -0.8032 0.06158 0.05331 -0.0267 1.0000 0.0619
-9.000 -0.8106 0.05771 0.04906 -0.0243 1.0000 0.0630
-8.750 -0.8154 0.05401 0.04482 -0.0215 1.0000 0.0646
-8.500 -0.8156 0.05059 0.04088 -0.0187 1.0000 0.0661
-8.250 -0.8048 0.04783 0.03799 -0.0172 1.0000 0.0679
-8.000 -0.7934 0.04518 0.03506 -0.0153 1.0000 0.0693
-7.750 -0.7804 0.04282 0.03241 -0.0135 1.0000 0.0715
-7.500 -0.7668 0.04067 0.02989 -0.0116 1.0000 0.0751
-7.250 -0.7515 0.03841 0.02711 -0.0096 1.0000 0.0781
-7.000 -0.7322 0.03616 0.02453 -0.0082 1.0000 0.0800
-6.750 -0.7109 0.03428 0.02252 -0.0072 1.0000 0.0824
-6.500 -0.6891 0.03270 0.02078 -0.0062 1.0000 0.0858
-6.250 -0.6670 0.03135 0.01915 -0.0051 1.0000 0.0915
-6.000 -0.6434 0.02994 0.01770 -0.0043 1.0000 0.0964
-5.750 -0.6191 0.02868 0.01635 -0.0035 1.0000 0.1013
-5.500 -0.5943 0.02756 0.01503 -0.0025 1.0000 0.1075
-5.250 -0.5729 0.02645 0.01397 -0.0014 1.0000 0.1150
-5.000 -0.5527 0.02547 0.01299 -0.0001 1.0000 0.1276
-4.750 -0.5340 0.02449 0.01207 0.0014 1.0000 0.1465
-4.500 -0.5166 0.02341 0.01113 0.0031 1.0000 0.1733
-4.000 -0.4908 0.02061 0.00952 0.0074 1.0000 0.3395
-3.750 -0.4827 0.01919 0.00951 0.0120 1.0000 0.5714
-3.500 -0.4534 0.01935 0.01013 0.0146 1.0000 0.7361
-3.250 -0.4216 0.01983 0.01053 0.0159 1.0000 0.8088
-3.000 -0.3796 0.02058 0.01107 0.0155 1.0000 0.8653
-2.750 -0.3209 0.02132 0.01146 0.0114 1.0000 0.9063
-2.500 -0.2444 0.02173 0.01150 0.0029 1.0000 0.9381
-2.250 -0.1882 0.02165 0.01117 -0.0028 1.0000 0.9598
-2.000 -0.1443 0.02137 0.01071 -0.0067 1.0000 0.9733
-1.750 -0.1013 0.02105 0.01025 -0.0105 1.0000 0.9849
-1.500 -0.0585 0.02069 0.00979 -0.0145 1.0000 0.9952
-1.250 -0.0334 0.02042 0.00947 -0.0151 1.0000 1.0000
-1.000 -0.0253 0.02026 0.00929 -0.0124 1.0000 1.0000
-0.750 -0.0180 0.02013 0.00916 -0.0095 1.0000 1.0000
-0.500 -0.0116 0.02005 0.00907 -0.0064 1.0000 1.0000
-0.250 -0.0056 0.02000 0.00902 -0.0032 1.0000 1.0000
0.000 0.0000 0.01998 0.00900 0.0000 1.0000 1.0000
0.250 0.0056 0.02000 0.00902 0.0032 1.0000 1.0000
0.500 0.0115 0.02005 0.00907 0.0064 1.0000 1.0000
0.750 0.0180 0.02013 0.00916 0.0095 1.0000 1.0000
1.000 0.0253 0.02025 0.00929 0.0124 1.0000 1.0000
1.250 0.0334 0.02041 0.00946 0.0151 1.0000 1.0000
1.500 0.0585 0.02068 0.00978 0.0145 0.9952 1.0000
1.750 0.1013 0.02104 0.01025 0.0105 0.9849 1.0000
2.000 0.1443 0.02137 0.01071 0.0067 0.9733 1.0000
2.250 0.1881 0.02165 0.01117 0.0028 0.9599 1.0000
2.500 0.2443 0.02173 0.01149 -0.0029 0.9382 1.0000
2.750 0.3209 0.02132 0.01146 -0.0114 0.9063 1.0000
3.000 0.3796 0.02058 0.01106 -0.0155 0.8654 1.0000
3.250 0.4215 0.01983 0.01052 -0.0159 0.8089 1.0000
3.500 0.4534 0.01934 0.01013 -0.0146 0.7362 1.0000
3.750 0.4827 0.01918 0.00951 -0.0120 0.5717 1.0000
4.000 0.4908 0.02060 0.00951 -0.0074 0.3397 1.0000
4.500 0.5166 0.02341 0.01113 -0.0031 0.1734 1.0000
4.750 0.5340 0.02449 0.01207 -0.0014 0.1464 1.0000
5.000 0.5527 0.02547 0.01299 0.0001 0.1276 1.0000
5.250 0.5729 0.02645 0.01397 0.0014 0.1150 1.0000
5.500 0.5943 0.02756 0.01502 0.0025 0.1075 1.0000
5.750 0.6191 0.02868 0.01635 0.0035 0.1013 1.0000
6.000 0.6434 0.02994 0.01770 0.0043 0.0964 1.0000
6.250 0.6670 0.03135 0.01915 0.0051 0.0915 1.0000
6.500 0.6891 0.03270 0.02078 0.0062 0.0858 1.0000
6.750 0.7109 0.03428 0.02252 0.0072 0.0824 1.0000
7.000 0.7322 0.03616 0.02453 0.0082 0.0800 1.0000
7.250 0.7515 0.03841 0.02711 0.0096 0.0781 1.0000
7.500 0.7668 0.04066 0.02989 0.0116 0.0751 1.0000
7.750 0.7804 0.04281 0.03241 0.0135 0.0715 1.0000
8.000 0.7935 0.04518 0.03506 0.0153 0.0693 1.0000
8.250 0.8048 0.04783 0.03799 0.0172 0.0679 1.0000
8.500 0.8157 0.05059 0.04088 0.0187 0.0661 1.0000
8.750 0.8154 0.05402 0.04483 0.0215 0.0646 1.0000
9.000 0.8107 0.05772 0.04907 0.0243 0.0630 1.0000
9.250 0.8034 0.06159 0.05332 0.0266 0.0619 1.0000
9.500 0.7927 0.06567 0.05769 0.0287 0.0615 1.0000
9.750 0.7779 0.06992 0.06216 0.0303 0.0615 1.0000
10.000 0.7572 0.07419 0.06653 0.0317 0.0616 1.0000
10.250 0.7345 0.07907 0.07151 0.0315 0.0620 1.0000
10.500 0.7124 0.08506 0.07755 0.0289 0.0625 1.0000
10.750 0.6936 0.09218 0.08468 0.0244 0.0631 1.0000
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Polar data table (+)
Polar graphs
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