NACA 64A-010 10.0% (naca64a010-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64A-010 10.0% (naca64a010-il) Reynolds number: 100,000 Max Cl/Cd: 34.52 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64a010-il-100000-n5.txt Download as CSV file: xf-naca64a010-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.6744 0.08761 0.08238 -0.0232 1.0000 0.0259
-10.750 -0.6865 0.08151 0.07625 -0.0269 1.0000 0.0256
-10.500 -0.7020 0.07584 0.07053 -0.0302 1.0000 0.0255
-10.250 -0.7187 0.07096 0.06556 -0.0323 1.0000 0.0253
-10.000 -0.7359 0.06681 0.06130 -0.0329 1.0000 0.0252
-9.750 -0.7530 0.06319 0.05755 -0.0318 1.0000 0.0251
-9.500 -0.7674 0.05989 0.05409 -0.0296 1.0000 0.0250
-9.250 -0.7769 0.05632 0.05029 -0.0277 1.0000 0.0249
-9.000 -0.7831 0.05267 0.04636 -0.0255 1.0000 0.0250
-8.750 -0.7849 0.04917 0.04253 -0.0233 1.0000 0.0250
-8.500 -0.7835 0.04576 0.03873 -0.0210 1.0000 0.0251
-8.250 -0.7786 0.04252 0.03504 -0.0186 1.0000 0.0252
-8.000 -0.7703 0.03952 0.03159 -0.0164 1.0000 0.0255
-7.750 -0.7599 0.03664 0.02834 -0.0144 1.0000 0.0264
-7.500 -0.7458 0.03468 0.02626 -0.0131 1.0000 0.0279
-7.250 -0.7294 0.03291 0.02428 -0.0116 1.0000 0.0293
-7.000 -0.7116 0.03084 0.02192 -0.0101 1.0000 0.0302
-6.750 -0.6920 0.02883 0.01961 -0.0086 1.0000 0.0311
-6.500 -0.6711 0.02704 0.01758 -0.0073 1.0000 0.0322
-6.250 -0.6497 0.02547 0.01578 -0.0061 1.0000 0.0337
-6.000 -0.6293 0.02412 0.01429 -0.0048 1.0000 0.0361
-5.750 -0.6107 0.02290 0.01311 -0.0034 1.0000 0.0390
-5.500 -0.5920 0.02180 0.01197 -0.0018 1.0000 0.0412
-5.250 -0.5744 0.02080 0.01090 0.0001 1.0000 0.0439
-5.000 -0.5581 0.01988 0.00989 0.0021 1.0000 0.0475
-4.750 -0.5423 0.01909 0.00912 0.0040 1.0000 0.0535
-4.500 -0.5262 0.01838 0.00832 0.0061 1.0000 0.0597
-4.250 -0.5108 0.01764 0.00758 0.0082 1.0000 0.0700
-4.000 -0.4960 0.01686 0.00693 0.0103 1.0000 0.0906
-3.750 -0.4833 0.01586 0.00628 0.0126 1.0000 0.1515
-3.500 -0.4783 0.01412 0.00573 0.0158 1.0000 0.3673
-3.250 -0.4599 0.01332 0.00581 0.0174 0.9952 0.5670
-3.000 -0.4281 0.01319 0.00592 0.0170 0.9868 0.6534
-2.750 -0.3985 0.01326 0.00618 0.0175 0.9780 0.7256
-2.500 -0.3689 0.01342 0.00638 0.0181 0.9693 0.7756
-2.250 -0.3331 0.01346 0.00635 0.0168 0.9621 0.7954
-2.000 -0.2971 0.01342 0.00620 0.0151 0.9541 0.8085
-1.750 -0.2610 0.01337 0.00602 0.0134 0.9462 0.8202
-1.500 -0.2218 0.01335 0.00591 0.0111 0.9392 0.8297
-1.250 -0.1859 0.01331 0.00581 0.0094 0.9308 0.8399
-1.000 -0.1480 0.01326 0.00569 0.0073 0.9234 0.8507
-0.750 -0.1121 0.01325 0.00564 0.0057 0.9142 0.8601
-0.500 -0.0733 0.01323 0.00559 0.0035 0.9067 0.8693
-0.250 -0.0385 0.01321 0.00555 0.0021 0.8970 0.8798
0.000 0.0000 0.01322 0.00556 0.0000 0.8882 0.8882
0.250 0.0385 0.01321 0.00555 -0.0021 0.8798 0.8969
0.500 0.0733 0.01323 0.00559 -0.0035 0.8693 0.9067
0.750 0.1121 0.01325 0.00564 -0.0057 0.8600 0.9142
1.000 0.1480 0.01326 0.00569 -0.0073 0.8507 0.9234
1.250 0.1859 0.01331 0.00581 -0.0094 0.8399 0.9308
1.500 0.2219 0.01335 0.00592 -0.0111 0.8297 0.9393
1.750 0.2610 0.01337 0.00602 -0.0134 0.8201 0.9461
2.000 0.2971 0.01342 0.00620 -0.0151 0.8085 0.9541
2.250 0.3332 0.01346 0.00634 -0.0168 0.7954 0.9620
2.500 0.3688 0.01342 0.00638 -0.0181 0.7755 0.9693
2.750 0.3985 0.01326 0.00618 -0.0175 0.7254 0.9780
3.000 0.4282 0.01319 0.00592 -0.0170 0.6539 0.9868
3.250 0.4598 0.01332 0.00581 -0.0174 0.5664 0.9952
3.500 0.4784 0.01412 0.00573 -0.0158 0.3680 1.0000
3.750 0.4834 0.01586 0.00628 -0.0126 0.1514 1.0000
4.000 0.4961 0.01685 0.00693 -0.0104 0.0908 1.0000
4.250 0.5109 0.01764 0.00759 -0.0082 0.0697 1.0000
4.500 0.5263 0.01838 0.00832 -0.0061 0.0597 1.0000
4.750 0.5424 0.01909 0.00912 -0.0041 0.0533 1.0000
5.000 0.5581 0.01989 0.00990 -0.0021 0.0474 1.0000
5.250 0.5745 0.02081 0.01090 -0.0001 0.0438 1.0000
5.500 0.5920 0.02180 0.01197 0.0018 0.0412 1.0000
5.750 0.6107 0.02290 0.01311 0.0034 0.0388 1.0000
6.000 0.6293 0.02413 0.01430 0.0047 0.0361 1.0000
6.250 0.6497 0.02548 0.01578 0.0061 0.0336 1.0000
6.500 0.6711 0.02704 0.01758 0.0073 0.0322 1.0000
6.750 0.6920 0.02884 0.01962 0.0086 0.0311 1.0000
7.000 0.7116 0.03085 0.02193 0.0101 0.0301 1.0000
7.250 0.7294 0.03288 0.02425 0.0116 0.0292 1.0000
7.500 0.7457 0.03460 0.02615 0.0130 0.0277 1.0000
7.750 0.7602 0.03662 0.02834 0.0144 0.0265 1.0000
8.000 0.7703 0.03955 0.03161 0.0163 0.0256 1.0000
8.250 0.7786 0.04250 0.03502 0.0186 0.0252 1.0000
8.500 0.7835 0.04575 0.03873 0.0210 0.0251 1.0000
8.750 0.7850 0.04917 0.04252 0.0233 0.0250 1.0000
9.000 0.7830 0.05271 0.04640 0.0255 0.0249 1.0000
9.250 0.7774 0.05628 0.05025 0.0276 0.0250 1.0000
9.500 0.7671 0.05994 0.05414 0.0296 0.0250 1.0000
9.750 0.7539 0.06315 0.05750 0.0317 0.0251 1.0000
10.000 0.7363 0.06680 0.06128 0.0328 0.0252 1.0000
10.250 0.7197 0.07092 0.06551 0.0323 0.0253 1.0000
10.500 0.7026 0.07583 0.07052 0.0301 0.0255 1.0000
10.750 0.6868 0.08157 0.07631 0.0268 0.0257 1.0000
11.000 0.6753 0.08757 0.08233 0.0232 0.0259 1.0000
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Polar data table (+)
Polar graphs
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