BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il) Reynolds number: 50,000 Max Cl/Cd: 21.27 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b540ols-il-50000.txt Download as CSV file: xf-b540ols-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: BELL 540 AIRFOIL (MODIFIED NACA 0012)
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6663 0.11302 0.10568 0.0453 1.0000 0.3281
-8.500 -0.7694 0.08126 0.07400 0.0071 1.0000 0.1726
-8.250 -0.7697 0.07464 0.06730 0.0042 1.0000 0.1696
-8.000 -0.7758 0.06713 0.05964 0.0002 1.0000 0.1673
-7.750 -0.7822 0.05919 0.05137 -0.0038 1.0000 0.1657
-7.500 -0.7810 0.05229 0.04398 -0.0064 1.0000 0.1662
-7.250 -0.7728 0.04640 0.03745 -0.0079 1.0000 0.1687
-7.000 -0.7561 0.04261 0.03330 -0.0080 1.0000 0.1751
-6.750 -0.7358 0.03962 0.03000 -0.0079 1.0000 0.1832
-6.500 -0.7141 0.03698 0.02714 -0.0076 1.0000 0.1930
-6.250 -0.6918 0.03431 0.02410 -0.0074 1.0000 0.2051
-6.000 -0.6679 0.03235 0.02200 -0.0069 1.0000 0.2203
-5.750 -0.6434 0.03069 0.02031 -0.0062 1.0000 0.2377
-5.500 -0.6187 0.02924 0.01882 -0.0055 1.0000 0.2594
-5.250 -0.5940 0.02793 0.01754 -0.0047 1.0000 0.2845
-5.000 -0.5693 0.02683 0.01646 -0.0038 1.0000 0.3140
-4.750 -0.5447 0.02596 0.01567 -0.0027 1.0000 0.3460
-4.500 -0.5205 0.02521 0.01505 -0.0014 1.0000 0.3801
-4.250 -0.4964 0.02445 0.01441 0.0000 1.0000 0.4158
-4.000 -0.4725 0.02365 0.01372 0.0014 1.0000 0.4521
-3.750 -0.4486 0.02286 0.01298 0.0028 1.0000 0.4889
-3.500 -0.4247 0.02208 0.01228 0.0041 1.0000 0.5256
-3.250 -0.4011 0.02136 0.01170 0.0058 1.0000 0.5603
-3.000 -0.3777 0.02066 0.01113 0.0075 1.0000 0.5951
-2.750 -0.3549 0.02001 0.01060 0.0094 1.0000 0.6301
-2.500 -0.3323 0.01939 0.01011 0.0114 1.0000 0.6660
-2.250 -0.3099 0.01880 0.00964 0.0134 1.0000 0.7034
-2.000 -0.2883 0.01824 0.00922 0.0157 1.0000 0.7430
-1.750 -0.2675 0.01773 0.00890 0.0185 1.0000 0.7847
-1.500 -0.2447 0.01728 0.00863 0.0210 1.0000 0.8333
-1.250 -0.2063 0.01697 0.00842 0.0207 1.0000 0.8946
-1.000 -0.1066 0.01685 0.00815 0.0077 1.0000 0.9690
-0.750 -0.0472 0.01593 0.00714 -0.0020 1.0000 1.0000
-0.500 -0.0372 0.01542 0.00656 -0.0013 1.0000 1.0000
-0.250 -0.0197 0.01525 0.00632 -0.0006 1.0000 1.0000
0.000 0.0000 0.01521 0.00625 0.0000 1.0000 1.0000
0.250 0.0197 0.01525 0.00632 0.0006 1.0000 1.0000
0.500 0.0372 0.01542 0.00656 0.0013 1.0000 1.0000
0.750 0.0472 0.01593 0.00714 0.0020 1.0000 1.0000
1.000 0.1065 0.01685 0.00815 -0.0077 0.9691 1.0000
1.250 0.2063 0.01697 0.00842 -0.0207 0.8947 1.0000
1.500 0.2448 0.01728 0.00863 -0.0210 0.8333 1.0000
1.750 0.2675 0.01773 0.00890 -0.0185 0.7847 1.0000
2.000 0.2883 0.01824 0.00922 -0.0157 0.7430 1.0000
2.250 0.3100 0.01880 0.00964 -0.0134 0.7035 1.0000
2.500 0.3324 0.01939 0.01011 -0.0114 0.6660 1.0000
2.750 0.3550 0.02001 0.01060 -0.0094 0.6301 1.0000
3.000 0.3778 0.02066 0.01113 -0.0076 0.5951 1.0000
3.250 0.4012 0.02136 0.01170 -0.0058 0.5603 1.0000
3.500 0.4247 0.02208 0.01228 -0.0042 0.5256 1.0000
3.750 0.4486 0.02286 0.01298 -0.0028 0.4890 1.0000
4.000 0.4726 0.02365 0.01372 -0.0014 0.4522 1.0000
4.250 0.4965 0.02445 0.01441 0.0000 0.4158 1.0000
4.500 0.5205 0.02521 0.01505 0.0014 0.3801 1.0000
4.750 0.5448 0.02596 0.01567 0.0027 0.3461 1.0000
5.000 0.5693 0.02683 0.01646 0.0038 0.3140 1.0000
5.250 0.5941 0.02793 0.01754 0.0047 0.2845 1.0000
5.500 0.6188 0.02924 0.01882 0.0055 0.2594 1.0000
5.750 0.6434 0.03069 0.02031 0.0062 0.2378 1.0000
6.000 0.6680 0.03235 0.02200 0.0068 0.2203 1.0000
6.250 0.6919 0.03431 0.02410 0.0073 0.2051 1.0000
6.500 0.7142 0.03698 0.02714 0.0076 0.1930 1.0000
6.750 0.7359 0.03962 0.03000 0.0079 0.1832 1.0000
7.000 0.7561 0.04261 0.03330 0.0080 0.1751 1.0000
7.250 0.7729 0.04640 0.03745 0.0078 0.1687 1.0000
7.500 0.7811 0.05229 0.04398 0.0063 0.1662 1.0000
7.750 0.7823 0.05920 0.05138 0.0038 0.1657 1.0000
8.000 0.7760 0.06713 0.05964 -0.0002 0.1673 1.0000
8.250 0.7699 0.07465 0.06730 -0.0042 0.1696 1.0000
8.500 0.7697 0.08127 0.07400 -0.0072 0.1726 1.0000
8.750 0.6677 0.11311 0.10577 -0.0454 0.3280 1.0000
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Polar data table (+)
Polar graphs
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