NACA 0008 (naca0008-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0008 (naca0008-il) Reynolds number: 100,000 Max Cl/Cd: 34.55 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca0008-il-100000.txt Download as CSV file: xf-naca0008-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0008
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5657 0.09227 0.08768 0.0037 1.0000 0.1506
-9.000 -0.5968 0.08657 0.08208 -0.0018 1.0000 0.1523
-8.750 -0.7155 0.08997 0.08534 0.0035 1.0000 0.1405
-8.500 -0.6980 0.08727 0.08260 0.0072 1.0000 0.1461
-7.750 -0.7635 0.05433 0.04844 -0.0150 1.0000 0.0842
-7.500 -0.7567 0.04621 0.03951 -0.0139 1.0000 0.0679
-7.250 -0.7443 0.04127 0.03418 -0.0129 1.0000 0.0666
-7.000 -0.7295 0.03756 0.02981 -0.0114 1.0000 0.0680
-6.750 -0.7128 0.03389 0.02551 -0.0100 1.0000 0.0699
-6.500 -0.6925 0.03043 0.02174 -0.0091 1.0000 0.0724
-6.250 -0.6698 0.02856 0.01967 -0.0083 1.0000 0.0788
-6.000 -0.6461 0.02650 0.01702 -0.0070 1.0000 0.0831
-5.750 -0.6224 0.02439 0.01495 -0.0065 1.0000 0.0906
-5.500 -0.5970 0.02293 0.01315 -0.0056 1.0000 0.0969
-5.250 -0.5724 0.02125 0.01153 -0.0050 1.0000 0.1045
-5.000 -0.5476 0.01991 0.01014 -0.0042 1.0000 0.1134
-4.750 -0.5232 0.01871 0.00893 -0.0032 1.0000 0.1233
-4.500 -0.5004 0.01744 0.00779 -0.0021 1.0000 0.1392
-4.250 -0.4799 0.01598 0.00669 -0.0008 1.0000 0.1789
-4.000 -0.4646 0.01393 0.00582 0.0010 1.0000 0.3548
-3.750 -0.4471 0.01294 0.00553 0.0032 1.0000 0.5049
-3.500 -0.4272 0.01239 0.00535 0.0054 1.0000 0.6034
-3.250 -0.4074 0.01201 0.00528 0.0080 1.0000 0.6924
-3.000 -0.3881 0.01184 0.00537 0.0114 1.0000 0.7806
-2.750 -0.3652 0.01191 0.00552 0.0144 1.0000 0.8508
-2.500 -0.3298 0.01214 0.00566 0.0147 1.0000 0.9037
-2.250 -0.2728 0.01247 0.00575 0.0102 1.0000 0.9441
-2.000 -0.1988 0.01262 0.00562 0.0015 1.0000 0.9717
-1.750 -0.1253 0.01247 0.00523 -0.0080 1.0000 0.9946
-1.500 -0.0917 0.01211 0.00478 -0.0103 1.0000 1.0000
-1.250 -0.0747 0.01182 0.00444 -0.0093 1.0000 1.0000
-1.000 -0.0582 0.01160 0.00418 -0.0080 1.0000 1.0000
-0.750 -0.0424 0.01144 0.00399 -0.0063 1.0000 1.0000
-0.500 -0.0276 0.01133 0.00387 -0.0044 1.0000 1.0000
-0.250 -0.0137 0.01126 0.00379 -0.0022 1.0000 1.0000
0.000 0.0000 0.01124 0.00377 0.0000 1.0000 1.0000
0.250 0.0137 0.01126 0.00379 0.0022 1.0000 1.0000
0.500 0.0276 0.01133 0.00387 0.0044 1.0000 1.0000
0.750 0.0424 0.01144 0.00399 0.0063 1.0000 1.0000
1.000 0.0582 0.01160 0.00418 0.0080 1.0000 1.0000
1.250 0.0748 0.01182 0.00444 0.0093 1.0000 1.0000
1.500 0.0917 0.01211 0.00478 0.0103 1.0000 1.0000
1.750 0.1253 0.01247 0.00523 0.0080 0.9946 1.0000
2.000 0.1988 0.01262 0.00562 -0.0015 0.9717 1.0000
2.250 0.2728 0.01247 0.00575 -0.0102 0.9441 1.0000
2.500 0.3298 0.01214 0.00566 -0.0147 0.9038 1.0000
2.750 0.3652 0.01191 0.00552 -0.0144 0.8509 1.0000
3.000 0.3881 0.01184 0.00537 -0.0114 0.7806 1.0000
3.250 0.4074 0.01201 0.00528 -0.0080 0.6924 1.0000
3.500 0.4273 0.01239 0.00535 -0.0054 0.6034 1.0000
3.750 0.4471 0.01294 0.00553 -0.0032 0.5049 1.0000
4.250 0.4799 0.01598 0.00669 0.0008 0.1789 1.0000
4.500 0.5004 0.01744 0.00779 0.0021 0.1392 1.0000
4.750 0.5232 0.01871 0.00893 0.0032 0.1233 1.0000
5.000 0.5476 0.01991 0.01014 0.0042 0.1134 1.0000
5.250 0.5724 0.02125 0.01153 0.0050 0.1045 1.0000
5.500 0.5970 0.02294 0.01315 0.0056 0.0969 1.0000
5.750 0.6224 0.02439 0.01495 0.0065 0.0906 1.0000
6.000 0.6461 0.02650 0.01703 0.0070 0.0831 1.0000
6.250 0.6698 0.02856 0.01967 0.0083 0.0788 1.0000
6.500 0.6925 0.03043 0.02174 0.0091 0.0724 1.0000
6.750 0.7128 0.03390 0.02552 0.0100 0.0699 1.0000
7.000 0.7295 0.03757 0.02982 0.0114 0.0680 1.0000
7.250 0.7443 0.04127 0.03418 0.0129 0.0666 1.0000
7.500 0.7567 0.04621 0.03951 0.0139 0.0679 1.0000
7.750 0.7636 0.05433 0.04843 0.0150 0.0842 1.0000
8.500 0.6984 0.08728 0.08262 -0.0073 0.1461 1.0000
8.750 0.7192 0.08972 0.08510 -0.0025 0.1403 1.0000
9.000 0.7106 0.09575 0.09106 -0.0062 0.1377 1.0000
9.250 0.5654 0.09211 0.08752 -0.0037 0.1507 1.0000
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Polar data table (+)
Polar graphs
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