NACA 0008 (naca0008-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0008 (naca0008-il) Reynolds number: 200,000 Max Cl/Cd: 38.52 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca0008-il-200000-n5.txt Download as CSV file: xf-naca0008-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.7808 0.09050 0.08710 0.0095 1.0000 0.0131
-10.500 -0.8455 0.06451 0.06109 -0.0106 1.0000 0.0119
-10.250 -0.8812 0.05527 0.05156 -0.0172 1.0000 0.0116
-10.000 -0.9046 0.04947 0.04544 -0.0171 1.0000 0.0116
-9.750 -0.9151 0.04434 0.03990 -0.0165 1.0000 0.0118
-9.500 -0.9164 0.03998 0.03510 -0.0153 1.0000 0.0120
-9.250 -0.9110 0.03627 0.03095 -0.0141 1.0000 0.0125
-9.000 -0.8996 0.03341 0.02768 -0.0130 1.0000 0.0133
-8.750 -0.8848 0.03091 0.02476 -0.0118 1.0000 0.0142
-8.500 -0.8675 0.02872 0.02215 -0.0108 1.0000 0.0149
-8.250 -0.8518 0.02600 0.01912 -0.0096 1.0000 0.0159
-8.000 -0.8311 0.02469 0.01762 -0.0089 1.0000 0.0169
-7.750 -0.8093 0.02357 0.01634 -0.0082 1.0000 0.0182
-7.500 -0.7865 0.02256 0.01514 -0.0075 1.0000 0.0203
-7.250 -0.7634 0.02146 0.01380 -0.0068 1.0000 0.0224
-7.000 -0.7418 0.02002 0.01222 -0.0059 1.0000 0.0242
-6.750 -0.7186 0.01924 0.01140 -0.0053 1.0000 0.0270
-6.500 -0.6946 0.01854 0.01058 -0.0047 1.0000 0.0304
-6.250 -0.6704 0.01788 0.00972 -0.0041 1.0000 0.0328
-6.000 -0.6482 0.01686 0.00870 -0.0034 1.0000 0.0367
-5.750 -0.6241 0.01626 0.00803 -0.0028 1.0000 0.0401
-5.500 -0.5996 0.01576 0.00742 -0.0022 1.0000 0.0431
-5.250 -0.5767 0.01497 0.00662 -0.0014 1.0000 0.0468
-5.000 -0.5525 0.01445 0.00604 -0.0008 1.0000 0.0508
-4.750 -0.5281 0.01400 0.00550 -0.0002 1.0000 0.0549
-4.500 -0.5042 0.01345 0.00495 0.0005 1.0000 0.0603
-4.250 -0.4798 0.01303 0.00450 0.0012 1.0000 0.0690
-4.000 -0.4559 0.01253 0.00407 0.0018 1.0000 0.0871
-3.750 -0.4322 0.01202 0.00371 0.0025 1.0000 0.1203
-3.500 -0.4086 0.01152 0.00340 0.0031 1.0000 0.1665
-3.250 -0.3853 0.01100 0.00314 0.0037 1.0000 0.2255
-3.000 -0.3621 0.01048 0.00291 0.0043 1.0000 0.2977
-2.750 -0.3390 0.00999 0.00275 0.0050 1.0000 0.3732
-2.500 -0.3159 0.00954 0.00262 0.0058 1.0000 0.4505
-2.250 -0.2930 0.00912 0.00252 0.0066 1.0000 0.5291
-2.000 -0.2701 0.00875 0.00249 0.0077 1.0000 0.6060
-1.750 -0.2472 0.00845 0.00248 0.0089 1.0000 0.6771
-1.500 -0.2242 0.00823 0.00251 0.0101 1.0000 0.7387
-1.250 -0.1962 0.00809 0.00255 0.0104 0.9971 0.7931
-1.000 -0.1604 0.00803 0.00262 0.0091 0.9896 0.8398
-0.750 -0.1227 0.00803 0.00267 0.0074 0.9817 0.8787
-0.500 -0.0830 0.00805 0.00272 0.0053 0.9728 0.9092
-0.250 -0.0415 0.00807 0.00274 0.0027 0.9623 0.9319
0.000 0.0000 0.00807 0.00275 0.0000 0.9492 0.9492
0.250 0.0415 0.00807 0.00274 -0.0027 0.9319 0.9623
0.500 0.0830 0.00805 0.00272 -0.0053 0.9092 0.9728
0.750 0.1227 0.00803 0.00267 -0.0074 0.8787 0.9817
1.000 0.1604 0.00803 0.00261 -0.0091 0.8398 0.9896
1.250 0.1962 0.00809 0.00255 -0.0104 0.7931 0.9971
1.500 0.2242 0.00823 0.00250 -0.0101 0.7387 1.0000
1.750 0.2472 0.00845 0.00248 -0.0089 0.6773 1.0000
2.000 0.2702 0.00875 0.00249 -0.0077 0.6061 1.0000
2.250 0.2930 0.00912 0.00252 -0.0066 0.5291 1.0000
2.500 0.3159 0.00954 0.00262 -0.0058 0.4504 1.0000
2.750 0.3390 0.00999 0.00275 -0.0050 0.3733 1.0000
3.000 0.3621 0.01048 0.00291 -0.0043 0.2976 1.0000
3.250 0.3853 0.01101 0.00314 -0.0037 0.2253 1.0000
3.500 0.4087 0.01152 0.00340 -0.0031 0.1665 1.0000
3.750 0.4322 0.01202 0.00371 -0.0025 0.1203 1.0000
4.000 0.4559 0.01253 0.00407 -0.0018 0.0872 1.0000
4.250 0.4798 0.01303 0.00450 -0.0012 0.0690 1.0000
4.500 0.5042 0.01345 0.00495 -0.0005 0.0603 1.0000
4.750 0.5282 0.01400 0.00550 0.0002 0.0549 1.0000
5.000 0.5526 0.01445 0.00604 0.0008 0.0508 1.0000
5.250 0.5767 0.01497 0.00662 0.0014 0.0468 1.0000
5.500 0.5997 0.01576 0.00742 0.0022 0.0431 1.0000
5.750 0.6241 0.01626 0.00803 0.0028 0.0401 1.0000
6.000 0.6482 0.01686 0.00870 0.0034 0.0367 1.0000
6.250 0.6703 0.01788 0.00973 0.0041 0.0328 1.0000
6.500 0.6946 0.01854 0.01057 0.0047 0.0304 1.0000
6.750 0.7186 0.01924 0.01139 0.0053 0.0270 1.0000
7.000 0.7418 0.02002 0.01222 0.0059 0.0242 1.0000
7.250 0.7634 0.02146 0.01380 0.0068 0.0224 1.0000
7.500 0.7865 0.02256 0.01514 0.0075 0.0203 1.0000
7.750 0.8092 0.02356 0.01633 0.0082 0.0182 1.0000
8.000 0.8311 0.02469 0.01762 0.0089 0.0169 1.0000
8.250 0.8518 0.02599 0.01912 0.0096 0.0159 1.0000
8.500 0.8675 0.02872 0.02215 0.0108 0.0149 1.0000
8.750 0.8848 0.03091 0.02476 0.0118 0.0142 1.0000
9.000 0.8996 0.03341 0.02768 0.0130 0.0133 1.0000
9.250 0.9111 0.03626 0.03094 0.0141 0.0125 1.0000
9.500 0.9164 0.03998 0.03511 0.0153 0.0120 1.0000
9.750 0.9152 0.04433 0.03989 0.0164 0.0118 1.0000
10.000 0.9047 0.04949 0.04545 0.0171 0.0116 1.0000
10.250 0.8812 0.05531 0.05160 0.0171 0.0116 1.0000
10.500 0.8450 0.06474 0.06132 0.0103 0.0120 1.0000
10.750 0.7811 0.09065 0.08725 -0.0097 0.0131 1.0000
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Polar data table (+)
Polar graphs
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