NACA 0008-34 (naca000834-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0008-34 (naca000834-il) Reynolds number: 200,000 Max Cl/Cd: 40.52 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca000834-il-200000.txt Download as CSV file: xf-naca000834-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0008-34
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6666 0.08552 0.08187 -0.0223 1.0000 0.0288
-8.750 -0.6757 0.08186 0.07811 -0.0224 1.0000 0.0289
-8.500 -0.6911 0.07405 0.07027 -0.0232 1.0000 0.0295
-8.250 -0.6913 0.06873 0.06500 -0.0230 1.0000 0.0304
-8.000 -0.6893 0.06512 0.06136 -0.0224 1.0000 0.0314
-7.750 -0.6872 0.06160 0.05776 -0.0218 1.0000 0.0326
-7.500 -0.6841 0.05801 0.05403 -0.0210 1.0000 0.0340
-7.250 -0.6796 0.05437 0.05019 -0.0199 1.0000 0.0360
-7.000 -0.6719 0.05130 0.04676 -0.0181 1.0000 0.0395
-6.500 -0.6603 0.04381 0.03887 -0.0146 1.0000 0.0457
-6.250 -0.6534 0.04357 0.03788 -0.0107 1.0000 0.0547
-6.000 -0.6404 0.03835 0.03291 -0.0104 1.0000 0.0583
-5.750 -0.6305 0.03679 0.03082 -0.0074 1.0000 0.0684
-5.500 -0.6144 0.03359 0.02774 -0.0063 1.0000 0.0733
-5.250 -0.6010 0.03141 0.02534 -0.0043 1.0000 0.0851
-5.000 -0.5863 0.02946 0.02324 -0.0025 1.0000 0.0995
-4.750 -0.5376 0.01237 0.00545 0.0020 1.0000 0.0394
-4.500 -0.5144 0.00936 0.00187 0.0043 1.0000 0.0307
-4.250 -0.4922 0.00838 0.00066 0.0060 1.0000 0.0294
-4.000 -0.4758 0.01809 0.00979 0.0071 1.0000 0.0301
-3.750 -0.4547 0.01664 0.00836 0.0082 1.0000 0.0350
-3.500 -0.4334 0.01543 0.00710 0.0098 1.0000 0.0361
-3.250 -0.4129 0.01445 0.00607 0.0113 1.0000 0.0386
-3.000 -0.3924 0.01355 0.00509 0.0128 1.0000 0.0429
-2.750 -0.3711 0.01275 0.00423 0.0139 1.0000 0.0593
-2.500 -0.3652 0.00902 0.00354 0.0174 1.0000 0.6962
-2.250 -0.3502 0.00895 0.00406 0.0223 1.0000 0.8751
-2.000 -0.3037 0.00988 0.00493 0.0215 1.0000 0.9556
-1.750 -0.2308 0.01029 0.00509 0.0128 1.0000 0.9696
-1.500 -0.1764 0.01033 0.00493 0.0070 1.0000 0.9760
-1.250 -0.1290 0.01031 0.00480 0.0025 1.0000 0.9838
-1.000 -0.0803 0.01023 0.00464 -0.0024 1.0000 0.9901
-0.750 -0.0333 0.01013 0.00448 -0.0070 1.0000 0.9964
-0.500 -0.0011 0.01001 0.00434 -0.0088 1.0000 1.0000
-0.250 0.0008 0.00995 0.00428 -0.0046 1.0000 1.0000
0.000 0.0000 0.00993 0.00426 0.0000 1.0000 1.0000
0.250 -0.0008 0.00995 0.00428 0.0046 1.0000 1.0000
0.500 0.0011 0.01001 0.00434 0.0088 1.0000 1.0000
0.750 0.0333 0.01013 0.00448 0.0070 0.9964 1.0000
1.000 0.0803 0.01023 0.00464 0.0024 0.9901 1.0000
1.250 0.1290 0.01030 0.00480 -0.0025 0.9838 1.0000
1.500 0.1764 0.01033 0.00493 -0.0070 0.9760 1.0000
1.750 0.2307 0.01029 0.00509 -0.0127 0.9696 1.0000
2.000 0.3043 0.00987 0.00492 -0.0216 0.9555 1.0000
2.250 0.3501 0.00894 0.00405 -0.0223 0.8750 1.0000
2.500 0.3651 0.00901 0.00354 -0.0174 0.6978 1.0000
2.750 0.3710 0.01275 0.00422 -0.0139 0.0594 1.0000
3.000 0.3923 0.01354 0.00508 -0.0128 0.0429 1.0000
3.250 0.4128 0.01444 0.00607 -0.0113 0.0386 1.0000
3.500 0.4333 0.01542 0.00710 -0.0097 0.0361 1.0000
3.750 0.4546 0.01664 0.00835 -0.0082 0.0350 1.0000
4.000 0.4758 0.01808 0.00977 -0.0070 0.0302 1.0000
4.250 0.4994 0.02075 0.01260 -0.0059 0.0291 1.0000
4.500 0.5226 0.02193 0.01396 -0.0044 0.0298 1.0000
4.750 0.5482 0.02415 0.01678 -0.0020 0.0374 1.0000
5.000 0.5716 0.01600 0.01026 0.0026 0.0985 1.0000
5.250 0.5838 0.01795 0.01235 0.0047 0.0847 1.0000
5.500 0.5942 0.02015 0.01478 0.0070 0.0736 1.0000
6.500 0.6603 0.04382 0.03889 0.0146 0.0458 1.0000
6.750 0.6701 0.04915 0.04393 0.0146 0.0419 1.0000
7.000 0.6719 0.05132 0.04677 0.0181 0.0395 1.0000
7.250 0.6796 0.05438 0.05020 0.0199 0.0360 1.0000
7.500 0.6842 0.05801 0.05403 0.0210 0.0340 1.0000
7.750 0.6874 0.06161 0.05776 0.0218 0.0325 1.0000
8.000 0.6894 0.06513 0.06137 0.0224 0.0314 1.0000
8.250 0.6915 0.06875 0.06501 0.0230 0.0304 1.0000
8.500 0.6912 0.07410 0.07032 0.0231 0.0295 1.0000
8.750 0.6759 0.08189 0.07813 0.0223 0.0289 1.0000
9.000 0.6668 0.08556 0.08191 0.0222 0.0288 1.0000
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Polar data table (+)
Polar graphs
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