BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il) Reynolds number: 200,000 Max Cl/Cd: 42.55 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b540ols-il-200000.txt Download as CSV file: xf-b540ols-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.8675 0.10077 0.09702 0.0203 1.0000 0.0479
-11.750 -0.8918 0.09023 0.08646 0.0145 1.0000 0.0468
-11.500 -0.9471 0.07321 0.06930 0.0004 1.0000 0.0453
-11.250 -0.9970 0.06095 0.05675 -0.0117 1.0000 0.0443
-11.000 -1.0321 0.05442 0.04987 -0.0136 1.0000 0.0437
-10.750 -1.0489 0.04885 0.04386 -0.0138 1.0000 0.0436
-10.500 -1.0515 0.04446 0.03906 -0.0134 1.0000 0.0439
-10.250 -1.0460 0.04084 0.03504 -0.0127 1.0000 0.0445
-10.000 -1.0353 0.03787 0.03167 -0.0120 1.0000 0.0456
-9.750 -1.0216 0.03529 0.02862 -0.0112 1.0000 0.0468
-9.500 -1.0057 0.03275 0.02564 -0.0104 1.0000 0.0479
-9.250 -0.9859 0.03026 0.02308 -0.0100 1.0000 0.0492
-9.000 -0.9639 0.02877 0.02151 -0.0095 1.0000 0.0507
-8.750 -0.9412 0.02736 0.01992 -0.0090 1.0000 0.0526
-8.500 -0.9179 0.02612 0.01843 -0.0084 1.0000 0.0549
-8.250 -0.8951 0.02433 0.01648 -0.0079 1.0000 0.0573
-8.000 -0.8709 0.02321 0.01538 -0.0075 1.0000 0.0599
-7.750 -0.8460 0.02220 0.01425 -0.0071 1.0000 0.0629
-7.500 -0.8211 0.02106 0.01296 -0.0066 1.0000 0.0664
-7.250 -0.7964 0.02002 0.01200 -0.0063 1.0000 0.0704
-7.000 -0.7705 0.01926 0.01111 -0.0059 1.0000 0.0749
-6.750 -0.7458 0.01815 0.01006 -0.0055 1.0000 0.0802
-6.500 -0.7195 0.01751 0.00936 -0.0051 1.0000 0.0867
-6.250 -0.6943 0.01658 0.00850 -0.0048 1.0000 0.0940
-6.000 -0.6682 0.01584 0.00775 -0.0044 1.0000 0.1033
-5.750 -0.6416 0.01524 0.00714 -0.0042 1.0000 0.1147
-5.500 -0.6155 0.01453 0.00652 -0.0039 1.0000 0.1294
-5.250 -0.5892 0.01385 0.00598 -0.0037 1.0000 0.1478
-5.000 -0.5623 0.01331 0.00551 -0.0035 1.0000 0.1717
-4.750 -0.5357 0.01276 0.00512 -0.0034 1.0000 0.1993
-4.500 -0.5088 0.01229 0.00479 -0.0032 1.0000 0.2295
-4.250 -0.4816 0.01191 0.00454 -0.0030 1.0000 0.2605
-4.000 -0.4544 0.01158 0.00433 -0.0029 1.0000 0.2908
-3.750 -0.4271 0.01131 0.00416 -0.0027 1.0000 0.3199
-3.500 -0.3996 0.01109 0.00402 -0.0024 1.0000 0.3475
-3.250 -0.3720 0.01091 0.00391 -0.0022 1.0000 0.3738
-3.000 -0.3446 0.01072 0.00379 -0.0020 1.0000 0.3976
-2.750 -0.3171 0.01053 0.00368 -0.0017 1.0000 0.4211
-2.500 -0.2897 0.01034 0.00356 -0.0014 1.0000 0.4435
-2.250 -0.2626 0.01012 0.00345 -0.0011 1.0000 0.4652
-2.000 -0.2355 0.00992 0.00336 -0.0008 1.0000 0.4881
-1.750 -0.2086 0.00970 0.00327 -0.0005 1.0000 0.5112
-1.500 -0.1819 0.00948 0.00320 -0.0001 1.0000 0.5354
-1.250 -0.1554 0.00925 0.00314 0.0004 1.0000 0.5623
-1.000 -0.1294 0.00902 0.00312 0.0009 1.0000 0.5937
-0.750 -0.1040 0.00876 0.00312 0.0015 1.0000 0.6320
-0.500 -0.0796 0.00847 0.00317 0.0024 1.0000 0.6846
-0.250 -0.0374 0.00811 0.00325 0.0001 0.9635 0.7741
0.000 0.0000 0.00792 0.00332 0.0000 0.8825 0.8825
0.250 0.0374 0.00811 0.00325 -0.0001 0.7742 0.9636
0.500 0.0797 0.00847 0.00317 -0.0025 0.6847 1.0000
0.750 0.1040 0.00876 0.00312 -0.0016 0.6320 1.0000
1.000 0.1294 0.00902 0.00312 -0.0009 0.5937 1.0000
1.250 0.1555 0.00925 0.00314 -0.0004 0.5623 1.0000
1.500 0.1820 0.00948 0.00320 0.0000 0.5355 1.0000
1.750 0.2086 0.00970 0.00327 0.0004 0.5112 1.0000
2.000 0.2356 0.00992 0.00336 0.0008 0.4882 1.0000
2.250 0.2627 0.01012 0.00345 0.0011 0.4652 1.0000
2.500 0.2898 0.01034 0.00356 0.0014 0.4436 1.0000
2.750 0.3172 0.01053 0.00368 0.0017 0.4211 1.0000
3.000 0.3446 0.01072 0.00379 0.0020 0.3976 1.0000
3.250 0.3721 0.01091 0.00391 0.0022 0.3738 1.0000
3.500 0.3996 0.01109 0.00402 0.0024 0.3475 1.0000
3.750 0.4271 0.01131 0.00416 0.0026 0.3199 1.0000
4.000 0.4545 0.01158 0.00433 0.0028 0.2908 1.0000
4.250 0.4817 0.01191 0.00454 0.0030 0.2605 1.0000
4.500 0.5088 0.01229 0.00479 0.0032 0.2295 1.0000
4.750 0.5358 0.01276 0.00512 0.0033 0.1993 1.0000
5.000 0.5624 0.01331 0.00551 0.0035 0.1717 1.0000
5.250 0.5893 0.01385 0.00598 0.0037 0.1478 1.0000
5.500 0.6156 0.01453 0.00652 0.0039 0.1294 1.0000
5.750 0.6417 0.01524 0.00714 0.0042 0.1147 1.0000
6.000 0.6682 0.01584 0.00775 0.0044 0.1033 1.0000
6.250 0.6943 0.01658 0.00850 0.0048 0.0940 1.0000
6.500 0.7196 0.01751 0.00936 0.0051 0.0866 1.0000
6.750 0.7459 0.01815 0.01006 0.0054 0.0802 1.0000
7.000 0.7706 0.01926 0.01111 0.0058 0.0749 1.0000
7.250 0.7965 0.02002 0.01200 0.0062 0.0704 1.0000
7.500 0.8212 0.02107 0.01297 0.0066 0.0663 1.0000
7.750 0.8461 0.02220 0.01425 0.0071 0.0629 1.0000
8.000 0.8710 0.02321 0.01538 0.0075 0.0599 1.0000
8.250 0.8952 0.02433 0.01648 0.0079 0.0573 1.0000
8.500 0.9180 0.02613 0.01843 0.0084 0.0549 1.0000
8.750 0.9413 0.02736 0.01992 0.0090 0.0526 1.0000
9.000 0.9640 0.02878 0.02151 0.0095 0.0507 1.0000
9.250 0.9860 0.03026 0.02309 0.0100 0.0492 1.0000
9.500 1.0058 0.03274 0.02563 0.0104 0.0479 1.0000
9.750 1.0218 0.03529 0.02862 0.0112 0.0468 1.0000
10.000 1.0355 0.03786 0.03166 0.0120 0.0456 1.0000
10.250 1.0461 0.04084 0.03505 0.0127 0.0445 1.0000
10.500 1.0517 0.04446 0.03906 0.0133 0.0439 1.0000
10.750 1.0490 0.04886 0.04388 0.0138 0.0436 1.0000
11.000 1.0323 0.05444 0.04989 0.0136 0.0437 1.0000
11.250 0.9974 0.06097 0.05677 0.0116 0.0442 1.0000
11.500 0.9471 0.07338 0.06948 -0.0007 0.0453 1.0000
11.750 0.8923 0.09035 0.08658 -0.0147 0.0468 1.0000
12.000 0.8683 0.10082 0.09707 -0.0205 0.0478 1.0000
12.500 0.7416 0.15050 0.14667 -0.0496 0.0703 1.0000
12.750 0.6109 0.14192 0.13834 -0.0245 0.0760 1.0000
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Polar data table (+)
Polar graphs
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