NACA 0008-34 (naca000834-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NACA 0008-34 (naca000834-il) Reynolds number: 50,000 Max Cl/Cd: 18.29 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca000834-il-50000.txt Download as CSV file: xf-naca000834-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6028 0.09888 0.09225 0.0228 1.0000 0.3919
-8.000 -0.6120 0.09666 0.09013 0.0242 1.0000 0.4155
-6.500 -0.6770 0.05895 0.05215 -0.0109 1.0000 0.2194
-6.250 -0.6660 0.05154 0.04369 -0.0137 1.0000 0.1556
-6.000 -0.6496 0.04671 0.03808 -0.0125 1.0000 0.1295
-5.750 -0.6310 0.04269 0.03343 -0.0108 1.0000 0.1152
-5.500 -0.6109 0.03949 0.02939 -0.0085 1.0000 0.1049
-5.250 -0.5886 0.03604 0.02559 -0.0070 1.0000 0.1002
-5.000 -0.5640 0.03318 0.02214 -0.0053 1.0000 0.0963
-4.750 -0.5374 0.03073 0.01909 -0.0038 1.0000 0.0951
-4.500 -0.5109 0.02849 0.01673 -0.0029 1.0000 0.1025
-4.250 -0.4810 0.02630 0.01442 -0.0022 1.0000 0.1102
-4.000 -0.2329 0.02233 0.01288 -0.0221 1.0000 1.0000
-3.750 -0.2179 0.02145 0.01168 -0.0220 1.0000 1.0000
-3.500 -0.2024 0.02069 0.01065 -0.0217 1.0000 1.0000
-3.250 -0.1864 0.02004 0.00975 -0.0213 1.0000 1.0000
-3.000 -0.1701 0.01947 0.00896 -0.0207 1.0000 1.0000
-2.750 -0.1538 0.01899 0.00828 -0.0199 1.0000 1.0000
-2.500 -0.1374 0.01857 0.00762 -0.0190 1.0000 1.0000
-2.250 -0.1212 0.01821 0.00712 -0.0178 1.0000 1.0000
-2.000 -0.1054 0.01790 0.00668 -0.0166 1.0000 1.0000
-1.750 -0.0901 0.01764 0.00632 -0.0151 1.0000 1.0000
-1.500 -0.0754 0.01741 0.00602 -0.0134 1.0000 1.0000
-1.250 -0.0615 0.01723 0.00577 -0.0115 1.0000 1.0000
-1.000 -0.0484 0.01709 0.00558 -0.0095 1.0000 1.0000
-0.750 -0.0359 0.01698 0.00541 -0.0072 1.0000 1.0000
-0.500 -0.0237 0.01690 0.00531 -0.0049 1.0000 1.0000
-0.250 -0.0117 0.01685 0.00525 -0.0025 1.0000 1.0000
0.000 0.0000 0.01683 0.00523 0.0000 1.0000 1.0000
0.250 0.0118 0.01685 0.00525 0.0025 1.0000 1.0000
0.500 0.0237 0.01690 0.00531 0.0049 1.0000 1.0000
0.750 0.0359 0.01697 0.00541 0.0072 1.0000 1.0000
1.000 0.0484 0.01709 0.00558 0.0095 1.0000 1.0000
1.250 0.0615 0.01723 0.00577 0.0115 1.0000 1.0000
1.500 0.0754 0.01741 0.00601 0.0134 1.0000 1.0000
1.750 0.0901 0.01763 0.00631 0.0151 1.0000 1.0000
2.000 0.1055 0.01790 0.00668 0.0166 1.0000 1.0000
2.250 0.1213 0.01820 0.00711 0.0178 1.0000 1.0000
2.500 0.1375 0.01856 0.00762 0.0189 1.0000 1.0000
2.750 0.1539 0.01898 0.00828 0.0199 1.0000 1.0000
3.000 0.1703 0.01947 0.00896 0.0207 1.0000 1.0000
3.250 0.1865 0.02003 0.00974 0.0213 1.0000 1.0000
3.500 0.2026 0.02068 0.01064 0.0217 1.0000 1.0000
3.750 0.2181 0.02144 0.01168 0.0220 1.0000 1.0000
4.000 0.2332 0.02232 0.01287 0.0221 1.0000 1.0000
4.250 0.4810 0.02630 0.01442 0.0022 0.1102 1.0000
4.500 0.5109 0.02849 0.01673 0.0029 0.1025 1.0000
4.750 0.5374 0.03073 0.01909 0.0038 0.0950 1.0000
5.000 0.5639 0.03317 0.02214 0.0053 0.0963 1.0000
5.250 0.5885 0.03604 0.02559 0.0070 0.1002 1.0000
5.500 0.6108 0.03949 0.02939 0.0085 0.1049 1.0000
5.750 0.6310 0.04269 0.03343 0.0108 0.1152 1.0000
6.000 0.6496 0.04671 0.03808 0.0125 0.1295 1.0000
6.250 0.6660 0.05154 0.04369 0.0137 0.1556 1.0000
6.500 0.6770 0.05896 0.05215 0.0109 0.2195 1.0000
6.750 0.6110 0.05296 0.04699 0.0113 0.2442 1.0000
7.000 0.5721 0.06200 0.05615 0.0036 0.2979 1.0000
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Polar data table (+)
Polar graphs
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