NACA 0008 (naca0008-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0008 (naca0008-il) Reynolds number: 500,000 Max Cl/Cd: 50.19 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca0008-il-500000.txt Download as CSV file: xf-naca0008-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.9223 0.05195 0.04936 -0.0182 1.0000 0.0104
-10.500 -0.9411 0.04749 0.04468 -0.0183 1.0000 0.0104
-10.250 -0.9556 0.04279 0.03965 -0.0172 1.0000 0.0103
-10.000 -0.9645 0.03782 0.03427 -0.0157 1.0000 0.0104
-9.750 -0.9671 0.03305 0.02904 -0.0140 1.0000 0.0105
-9.500 -0.9605 0.02943 0.02502 -0.0125 1.0000 0.0108
-9.250 -0.9448 0.02751 0.02289 -0.0115 1.0000 0.0112
-9.000 -0.9238 0.02675 0.02204 -0.0110 1.0000 0.0119
-8.750 -0.9034 0.02563 0.02077 -0.0103 1.0000 0.0126
-8.500 -0.8839 0.02395 0.01886 -0.0094 1.0000 0.0133
-8.250 -0.8640 0.02214 0.01678 -0.0083 1.0000 0.0139
-8.000 -0.8422 0.02077 0.01520 -0.0075 1.0000 0.0145
-7.750 -0.8201 0.01943 0.01363 -0.0066 1.0000 0.0151
-7.500 -0.8022 0.01694 0.01091 -0.0053 1.0000 0.0170
-7.250 -0.7771 0.01661 0.01055 -0.0049 1.0000 0.0188
-7.000 -0.7525 0.01604 0.00990 -0.0044 1.0000 0.0208
-6.750 -0.7273 0.01558 0.00935 -0.0038 1.0000 0.0226
-6.500 -0.7060 0.01420 0.00787 -0.0028 1.0000 0.0257
-6.250 -0.6807 0.01388 0.00752 -0.0024 1.0000 0.0292
-6.000 -0.6549 0.01364 0.00722 -0.0020 1.0000 0.0322
-5.750 -0.6328 0.01260 0.00612 -0.0011 1.0000 0.0361
-5.500 -0.6080 0.01224 0.00575 -0.0006 1.0000 0.0396
-5.250 -0.5831 0.01190 0.00536 0.0000 1.0000 0.0421
-5.000 -0.5583 0.01159 0.00498 0.0006 1.0000 0.0438
-4.750 -0.5354 0.01089 0.00423 0.0015 1.0000 0.0473
-4.500 -0.5111 0.01051 0.00384 0.0022 1.0000 0.0508
-4.250 -0.4865 0.01020 0.00350 0.0029 1.0000 0.0545
-4.000 -0.4623 0.00978 0.00309 0.0036 1.0000 0.0622
-3.750 -0.4382 0.00933 0.00274 0.0043 1.0000 0.0848
-3.500 -0.4153 0.00865 0.00243 0.0050 1.0000 0.1594
-3.250 -0.3916 0.00813 0.00222 0.0056 1.0000 0.2319
-3.000 -0.3676 0.00770 0.00205 0.0061 1.0000 0.3013
-2.750 -0.3432 0.00732 0.00192 0.0066 1.0000 0.3687
-2.500 -0.3186 0.00698 0.00183 0.0070 1.0000 0.4337
-2.250 -0.2937 0.00668 0.00176 0.0075 1.0000 0.4974
-2.000 -0.2688 0.00636 0.00173 0.0079 1.0000 0.5690
-1.750 -0.2437 0.00610 0.00172 0.0084 1.0000 0.6356
-1.500 -0.2147 0.00584 0.00173 0.0081 0.9986 0.7048
-1.250 -0.1771 0.00557 0.00175 0.0061 0.9942 0.7774
-1.000 -0.1420 0.00536 0.00179 0.0049 0.9882 0.8432
-0.750 -0.1059 0.00527 0.00183 0.0035 0.9823 0.8865
-0.500 -0.0686 0.00523 0.00185 0.0019 0.9757 0.9140
-0.250 -0.0346 0.00521 0.00185 0.0010 0.9651 0.9359
0.000 0.0000 0.00521 0.00186 0.0000 0.9521 0.9521
0.250 0.0346 0.00521 0.00185 -0.0010 0.9359 0.9651
0.500 0.0686 0.00523 0.00185 -0.0019 0.9139 0.9757
0.750 0.1059 0.00527 0.00183 -0.0035 0.8865 0.9823
1.000 0.1420 0.00536 0.00179 -0.0049 0.8433 0.9882
1.250 0.1771 0.00557 0.00175 -0.0061 0.7780 0.9942
1.500 0.2147 0.00584 0.00173 -0.0081 0.7047 0.9986
1.750 0.2437 0.00610 0.00172 -0.0084 0.6347 1.0000
2.000 0.2688 0.00636 0.00173 -0.0079 0.5686 1.0000
2.250 0.2937 0.00667 0.00176 -0.0075 0.4978 1.0000
2.500 0.3186 0.00698 0.00183 -0.0070 0.4337 1.0000
2.750 0.3432 0.00732 0.00192 -0.0066 0.3688 1.0000
3.000 0.3676 0.00770 0.00205 -0.0061 0.3011 1.0000
3.250 0.3917 0.00814 0.00222 -0.0056 0.2317 1.0000
3.500 0.4153 0.00865 0.00243 -0.0050 0.1594 1.0000
3.750 0.4382 0.00933 0.00274 -0.0043 0.0848 1.0000
4.000 0.4623 0.00978 0.00309 -0.0036 0.0622 1.0000
4.250 0.4865 0.01020 0.00350 -0.0029 0.0545 1.0000
4.500 0.5111 0.01050 0.00384 -0.0022 0.0509 1.0000
4.750 0.5354 0.01089 0.00423 -0.0015 0.0473 1.0000
5.000 0.5584 0.01159 0.00498 -0.0006 0.0438 1.0000
5.250 0.5832 0.01190 0.00536 0.0000 0.0421 1.0000
5.500 0.6081 0.01224 0.00575 0.0006 0.0396 1.0000
5.750 0.6329 0.01261 0.00613 0.0011 0.0361 1.0000
6.000 0.6550 0.01364 0.00722 0.0020 0.0322 1.0000
6.250 0.6807 0.01388 0.00753 0.0024 0.0292 1.0000
6.500 0.7060 0.01420 0.00787 0.0028 0.0257 1.0000
6.750 0.7273 0.01557 0.00934 0.0038 0.0226 1.0000
7.000 0.7525 0.01604 0.00990 0.0044 0.0209 1.0000
7.250 0.7771 0.01660 0.01055 0.0049 0.0188 1.0000
7.500 0.8022 0.01694 0.01091 0.0053 0.0170 1.0000
7.750 0.8201 0.01942 0.01362 0.0066 0.0151 1.0000
8.000 0.8422 0.02077 0.01520 0.0075 0.0145 1.0000
8.250 0.8640 0.02214 0.01679 0.0083 0.0139 1.0000
8.500 0.8838 0.02396 0.01887 0.0094 0.0133 1.0000
8.750 0.9034 0.02562 0.02076 0.0103 0.0126 1.0000
9.000 0.9238 0.02675 0.02204 0.0110 0.0119 1.0000
9.250 0.9448 0.02749 0.02287 0.0115 0.0112 1.0000
9.500 0.9604 0.02942 0.02502 0.0125 0.0108 1.0000
9.750 0.9670 0.03306 0.02905 0.0140 0.0105 1.0000
10.000 0.9646 0.03780 0.03425 0.0157 0.0104 1.0000
10.250 0.9555 0.04282 0.03968 0.0172 0.0103 1.0000
10.500 0.9412 0.04751 0.04469 0.0182 0.0104 1.0000
10.750 0.9221 0.05202 0.04944 0.0181 0.0104 1.0000
11.000 0.8994 0.05928 0.05694 0.0122 0.0106 1.0000
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Polar data table (+)
Polar graphs
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