NACA 64A-010 10.0% (naca64a010-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64A-010 10.0% (naca64a010-il) Reynolds number: 50,000 Max Cl/Cd: 26.25 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64a010-il-50000-n5.txt Download as CSV file: xf-naca64a010-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6879 0.08881 0.08145 -0.0273 1.0000 0.0464
-10.250 -0.6984 0.08400 0.07661 -0.0292 1.0000 0.0462
-10.000 -0.7121 0.07964 0.07220 -0.0303 1.0000 0.0460
-9.750 -0.7262 0.07569 0.06817 -0.0302 1.0000 0.0458
-9.500 -0.7387 0.07209 0.06447 -0.0291 1.0000 0.0457
-9.250 -0.7485 0.06834 0.06055 -0.0281 1.0000 0.0455
-9.000 -0.7553 0.06456 0.05656 -0.0268 1.0000 0.0454
-8.750 -0.7586 0.06087 0.05261 -0.0253 1.0000 0.0453
-8.500 -0.7591 0.05724 0.04867 -0.0236 1.0000 0.0452
-8.250 -0.7567 0.05370 0.04477 -0.0218 1.0000 0.0453
-8.000 -0.7512 0.05028 0.04094 -0.0199 1.0000 0.0455
-7.750 -0.7425 0.04707 0.03727 -0.0180 1.0000 0.0458
-7.500 -0.7313 0.04409 0.03384 -0.0160 1.0000 0.0466
-7.250 -0.7166 0.04132 0.03097 -0.0150 1.0000 0.0490
-7.000 -0.6996 0.03912 0.02856 -0.0137 1.0000 0.0516
-6.750 -0.6803 0.03674 0.02578 -0.0124 1.0000 0.0537
-6.500 -0.6577 0.03443 0.02310 -0.0113 1.0000 0.0554
-6.250 -0.6324 0.03238 0.02068 -0.0103 1.0000 0.0579
-6.000 -0.6085 0.03056 0.01888 -0.0096 1.0000 0.0627
-5.750 -0.5844 0.02914 0.01730 -0.0086 1.0000 0.0689
-5.500 -0.5609 0.02769 0.01573 -0.0073 1.0000 0.0735
-5.250 -0.5425 0.02645 0.01443 -0.0057 1.0000 0.0820
-5.000 -0.5262 0.02524 0.01321 -0.0039 1.0000 0.0934
-4.750 -0.5114 0.02399 0.01198 -0.0017 1.0000 0.1068
-4.500 -0.4985 0.02259 0.01079 0.0005 1.0000 0.1379
-4.250 -0.4918 0.02037 0.00952 0.0030 1.0000 0.2528
-4.000 -0.4923 0.01876 0.00957 0.0087 1.0000 0.5412
-3.750 -0.4808 0.01874 0.00979 0.0135 1.0000 0.6521
-3.500 -0.4690 0.01910 0.01028 0.0189 1.0000 0.7334
-3.250 -0.4488 0.02006 0.01129 0.0244 1.0000 0.8052
-3.000 -0.4155 0.02055 0.01155 0.0255 1.0000 0.8381
-2.750 -0.3859 0.02048 0.01122 0.0253 1.0000 0.8544
-2.500 -0.3568 0.02036 0.01090 0.0250 1.0000 0.8691
-2.250 -0.3275 0.02023 0.01057 0.0243 1.0000 0.8827
-2.000 -0.2977 0.02009 0.01027 0.0234 1.0000 0.8959
-1.750 -0.2667 0.01998 0.00999 0.0221 1.0000 0.9090
-1.500 -0.2320 0.01989 0.00976 0.0201 1.0000 0.9211
-1.250 -0.1928 0.01982 0.00957 0.0170 1.0000 0.9320
-1.000 -0.1557 0.01975 0.00939 0.0142 1.0000 0.9439
-0.750 -0.1194 0.01969 0.00926 0.0114 1.0000 0.9566
-0.500 -0.0827 0.01965 0.00918 0.0083 1.0000 0.9699
-0.250 -0.0453 0.01963 0.00912 0.0049 1.0000 0.9840
0.000 0.0000 0.01961 0.00910 0.0000 0.9953 0.9953
0.250 0.0452 0.01963 0.00912 -0.0049 0.9840 1.0000
0.500 0.0827 0.01965 0.00917 -0.0083 0.9699 1.0000
0.750 0.1194 0.01969 0.00926 -0.0114 0.9566 1.0000
1.000 0.1557 0.01975 0.00939 -0.0142 0.9438 1.0000
1.250 0.1928 0.01982 0.00957 -0.0170 0.9320 1.0000
1.500 0.2319 0.01989 0.00976 -0.0200 0.9210 1.0000
1.750 0.2668 0.01998 0.00998 -0.0222 0.9090 1.0000
2.000 0.2977 0.02009 0.01027 -0.0234 0.8959 1.0000
2.250 0.3275 0.02023 0.01057 -0.0243 0.8827 1.0000
2.500 0.3568 0.02036 0.01089 -0.0250 0.8690 1.0000
2.750 0.3859 0.02048 0.01122 -0.0253 0.8544 1.0000
3.000 0.4154 0.02055 0.01155 -0.0255 0.8381 1.0000
3.250 0.4488 0.02006 0.01129 -0.0244 0.8051 1.0000
3.500 0.4691 0.01909 0.01028 -0.0189 0.7332 1.0000
3.750 0.4809 0.01874 0.00979 -0.0135 0.6527 1.0000
4.000 0.4924 0.01876 0.00957 -0.0087 0.5421 1.0000
4.250 0.4917 0.02039 0.00953 -0.0030 0.2510 1.0000
4.500 0.4985 0.02259 0.01080 -0.0005 0.1378 1.0000
4.750 0.5114 0.02400 0.01198 0.0017 0.1067 1.0000
5.000 0.5262 0.02524 0.01322 0.0039 0.0933 1.0000
5.250 0.5425 0.02645 0.01444 0.0057 0.0819 1.0000
5.500 0.5609 0.02769 0.01572 0.0073 0.0736 1.0000
5.750 0.5845 0.02915 0.01732 0.0086 0.0687 1.0000
6.000 0.6086 0.03058 0.01889 0.0096 0.0627 1.0000
6.250 0.6324 0.03238 0.02069 0.0103 0.0579 1.0000
6.500 0.6577 0.03443 0.02310 0.0113 0.0555 1.0000
6.750 0.6803 0.03675 0.02583 0.0124 0.0537 1.0000
7.000 0.6996 0.03912 0.02856 0.0138 0.0515 1.0000
7.250 0.7165 0.04130 0.03095 0.0150 0.0489 1.0000
7.500 0.7311 0.04417 0.03391 0.0160 0.0465 1.0000
7.750 0.7426 0.04705 0.03725 0.0179 0.0458 1.0000
8.000 0.7512 0.05028 0.04094 0.0199 0.0455 1.0000
8.250 0.7568 0.05369 0.04476 0.0218 0.0453 1.0000
8.500 0.7592 0.05724 0.04867 0.0236 0.0452 1.0000
8.750 0.7586 0.06087 0.05261 0.0253 0.0453 1.0000
9.000 0.7552 0.06458 0.05658 0.0268 0.0454 1.0000
9.250 0.7491 0.06832 0.06053 0.0281 0.0456 1.0000
9.500 0.7384 0.07212 0.06451 0.0291 0.0456 1.0000
9.750 0.7266 0.07568 0.06816 0.0302 0.0459 1.0000
10.000 0.7119 0.07964 0.07219 0.0303 0.0460 1.0000
10.250 0.7006 0.08398 0.07658 0.0293 0.0463 1.0000
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Polar data table (+)
Polar graphs
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