BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il) Reynolds number: 100,000 Max Cl/Cd: 31.54 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b540ols-il-100000.txt Download as CSV file: xf-b540ols-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.8494 0.08352 0.07832 -0.0002 1.0000 0.0882
-10.000 -0.8530 0.07779 0.07254 -0.0024 1.0000 0.0872
-9.750 -0.8655 0.07173 0.06643 -0.0048 1.0000 0.0862
-9.500 -0.8837 0.06453 0.05903 -0.0079 1.0000 0.0849
-9.250 -0.9005 0.05706 0.05118 -0.0102 1.0000 0.0836
-9.000 -0.9069 0.05051 0.04412 -0.0112 1.0000 0.0830
-8.750 -0.9036 0.04510 0.03815 -0.0114 1.0000 0.0831
-8.500 -0.8930 0.04084 0.03332 -0.0111 1.0000 0.0845
-8.250 -0.8784 0.03749 0.02928 -0.0105 1.0000 0.0871
-8.000 -0.8594 0.03438 0.02589 -0.0101 1.0000 0.0900
-7.750 -0.8367 0.03239 0.02379 -0.0097 1.0000 0.0933
-7.500 -0.8139 0.03050 0.02155 -0.0092 1.0000 0.0982
-7.250 -0.7905 0.02835 0.01917 -0.0087 1.0000 0.1031
-7.000 -0.7657 0.02689 0.01763 -0.0083 1.0000 0.1089
-6.750 -0.7407 0.02525 0.01578 -0.0078 1.0000 0.1162
-6.500 -0.7152 0.02402 0.01453 -0.0074 1.0000 0.1246
-6.250 -0.6898 0.02271 0.01323 -0.0070 1.0000 0.1343
-6.000 -0.6640 0.02151 0.01199 -0.0066 1.0000 0.1463
-5.750 -0.6383 0.02046 0.01099 -0.0062 1.0000 0.1612
-5.500 -0.6126 0.01949 0.01010 -0.0058 1.0000 0.1795
-5.250 -0.5866 0.01861 0.00924 -0.0054 1.0000 0.2030
-5.000 -0.5610 0.01781 0.00863 -0.0049 1.0000 0.2303
-4.750 -0.5352 0.01713 0.00810 -0.0045 1.0000 0.2620
-4.500 -0.5092 0.01658 0.00767 -0.0041 1.0000 0.2962
-4.250 -0.4832 0.01616 0.00741 -0.0036 1.0000 0.3295
-4.000 -0.4570 0.01584 0.00719 -0.0031 1.0000 0.3618
-3.750 -0.4306 0.01555 0.00696 -0.0026 1.0000 0.3932
-3.500 -0.4044 0.01522 0.00674 -0.0020 1.0000 0.4224
-3.250 -0.3782 0.01486 0.00650 -0.0014 1.0000 0.4502
-3.000 -0.3519 0.01450 0.00623 -0.0008 1.0000 0.4785
-2.750 -0.3257 0.01415 0.00598 -0.0003 1.0000 0.5069
-2.500 -0.2998 0.01376 0.00576 0.0004 1.0000 0.5340
-2.250 -0.2738 0.01339 0.00553 0.0011 1.0000 0.5625
-2.000 -0.2479 0.01303 0.00532 0.0018 1.0000 0.5927
-1.750 -0.2225 0.01267 0.00514 0.0026 1.0000 0.6245
-1.500 -0.1975 0.01230 0.00500 0.0036 1.0000 0.6592
-1.250 -0.1735 0.01192 0.00490 0.0049 1.0000 0.6988
-1.000 -0.1506 0.01156 0.00484 0.0066 1.0000 0.7498
-0.750 -0.1292 0.01123 0.00486 0.0090 1.0000 0.8206
-0.500 -0.0919 0.01105 0.00495 0.0085 1.0000 0.9247
-0.250 -0.0183 0.01098 0.00488 -0.0008 1.0000 1.0000
0.000 0.0000 0.01091 0.00476 0.0000 1.0000 1.0000
0.250 0.0183 0.01098 0.00488 0.0008 1.0000 1.0000
0.500 0.0919 0.01105 0.00495 -0.0085 0.9248 1.0000
0.750 0.1293 0.01123 0.00486 -0.0090 0.8207 1.0000
1.000 0.1507 0.01156 0.00484 -0.0066 0.7499 1.0000
1.250 0.1736 0.01192 0.00490 -0.0049 0.6989 1.0000
1.500 0.1975 0.01230 0.00500 -0.0036 0.6592 1.0000
1.750 0.2225 0.01267 0.00514 -0.0026 0.6245 1.0000
2.000 0.2480 0.01303 0.00532 -0.0018 0.5927 1.0000
2.250 0.2738 0.01339 0.00553 -0.0011 0.5625 1.0000
2.500 0.2998 0.01376 0.00576 -0.0005 0.5340 1.0000
2.750 0.3257 0.01415 0.00598 0.0002 0.5070 1.0000
3.000 0.3520 0.01450 0.00623 0.0008 0.4786 1.0000
3.250 0.3783 0.01486 0.00650 0.0014 0.4503 1.0000
3.500 0.4044 0.01522 0.00674 0.0020 0.4224 1.0000
3.750 0.4307 0.01555 0.00696 0.0026 0.3933 1.0000
4.000 0.4570 0.01584 0.00719 0.0031 0.3618 1.0000
4.250 0.4833 0.01616 0.00741 0.0036 0.3295 1.0000
4.500 0.5093 0.01658 0.00767 0.0041 0.2962 1.0000
4.750 0.5353 0.01713 0.00810 0.0045 0.2621 1.0000
5.000 0.5611 0.01781 0.00863 0.0049 0.2304 1.0000
5.250 0.5867 0.01860 0.00924 0.0053 0.2030 1.0000
5.500 0.6127 0.01949 0.01010 0.0057 0.1795 1.0000
5.750 0.6384 0.02046 0.01099 0.0062 0.1612 1.0000
6.000 0.6641 0.02151 0.01199 0.0066 0.1463 1.0000
6.250 0.6898 0.02270 0.01322 0.0070 0.1343 1.0000
6.500 0.7153 0.02402 0.01453 0.0074 0.1245 1.0000
6.750 0.7408 0.02525 0.01578 0.0078 0.1162 1.0000
7.000 0.7658 0.02689 0.01763 0.0083 0.1089 1.0000
7.250 0.7906 0.02835 0.01917 0.0087 0.1031 1.0000
7.500 0.8139 0.03049 0.02155 0.0091 0.0982 1.0000
7.750 0.8368 0.03239 0.02379 0.0097 0.0933 1.0000
8.000 0.8595 0.03438 0.02589 0.0101 0.0900 1.0000
8.250 0.8785 0.03749 0.02928 0.0105 0.0871 1.0000
8.500 0.8931 0.04084 0.03332 0.0110 0.0845 1.0000
8.750 0.9037 0.04510 0.03815 0.0113 0.0831 1.0000
9.000 0.9070 0.05051 0.04412 0.0112 0.0830 1.0000
9.250 0.9006 0.05707 0.05118 0.0102 0.0836 1.0000
9.500 0.8840 0.06454 0.05904 0.0079 0.0849 1.0000
9.750 0.8659 0.07175 0.06645 0.0047 0.0862 1.0000
10.000 0.8534 0.07782 0.07258 0.0023 0.0872 1.0000
10.250 0.8498 0.08355 0.07835 0.0001 0.0882 1.0000
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Polar data table (+)
Polar graphs
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