BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il) Reynolds number: 200,000 Max Cl/Cd: 44.91 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b540ols-il-200000-n5.txt Download as CSV file: xf-b540ols-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -1.0928 0.08584 0.08129 0.0115 1.0000 0.0242
-14.000 -1.1202 0.07648 0.07173 0.0050 1.0000 0.0242
-13.750 -1.1426 0.06822 0.06325 -0.0010 1.0000 0.0242
-13.500 -1.1599 0.06103 0.05586 -0.0065 1.0000 0.0242
-13.250 -1.1708 0.05533 0.04999 -0.0108 1.0000 0.0244
-13.000 -1.1783 0.05062 0.04511 -0.0142 1.0000 0.0245
-12.750 -1.1832 0.04692 0.04126 -0.0161 1.0000 0.0247
-12.500 -1.1863 0.04403 0.03823 -0.0165 1.0000 0.0249
-12.250 -1.1871 0.04177 0.03584 -0.0155 1.0000 0.0252
-12.000 -1.1816 0.03976 0.03369 -0.0148 1.0000 0.0256
-11.750 -1.1727 0.03791 0.03167 -0.0140 1.0000 0.0261
-11.500 -1.1615 0.03612 0.02970 -0.0133 1.0000 0.0268
-11.250 -1.1485 0.03435 0.02771 -0.0126 1.0000 0.0276
-11.000 -1.1337 0.03263 0.02574 -0.0118 1.0000 0.0283
-10.750 -1.1173 0.03101 0.02391 -0.0111 1.0000 0.0290
-10.500 -1.0995 0.02961 0.02245 -0.0104 1.0000 0.0297
-10.250 -1.0801 0.02843 0.02118 -0.0099 1.0000 0.0305
-10.000 -1.0597 0.02728 0.01994 -0.0093 1.0000 0.0314
-9.750 -1.0387 0.02615 0.01867 -0.0087 1.0000 0.0325
-9.500 -1.0168 0.02509 0.01744 -0.0082 1.0000 0.0338
-9.250 -0.9949 0.02402 0.01628 -0.0077 1.0000 0.0351
-9.000 -0.9720 0.02315 0.01537 -0.0073 1.0000 0.0366
-8.750 -0.9484 0.02232 0.01447 -0.0069 1.0000 0.0383
-8.500 -0.9245 0.02149 0.01350 -0.0065 1.0000 0.0401
-8.250 -0.9007 0.02061 0.01257 -0.0061 1.0000 0.0419
-8.000 -0.8761 0.01990 0.01184 -0.0058 1.0000 0.0442
-7.750 -0.8509 0.01924 0.01108 -0.0055 1.0000 0.0469
-7.500 -0.8259 0.01850 0.01029 -0.0051 1.0000 0.0496
-7.250 -0.8004 0.01787 0.00964 -0.0049 1.0000 0.0529
-7.000 -0.7743 0.01733 0.00902 -0.0046 1.0000 0.0566
-6.750 -0.7487 0.01667 0.00837 -0.0044 1.0000 0.0607
-6.500 -0.7222 0.01616 0.00782 -0.0041 1.0000 0.0657
-6.250 -0.6959 0.01560 0.00728 -0.0039 1.0000 0.0715
-6.000 -0.6691 0.01514 0.00678 -0.0037 1.0000 0.0784
-5.750 -0.6425 0.01464 0.00632 -0.0036 1.0000 0.0872
-5.500 -0.6156 0.01418 0.00589 -0.0034 1.0000 0.0973
-5.250 -0.5886 0.01374 0.00549 -0.0033 1.0000 0.1097
-5.000 -0.5615 0.01332 0.00513 -0.0031 1.0000 0.1245
-4.750 -0.5343 0.01293 0.00480 -0.0030 1.0000 0.1418
-4.500 -0.5070 0.01255 0.00449 -0.0029 1.0000 0.1611
-4.250 -0.4798 0.01218 0.00423 -0.0028 1.0000 0.1831
-4.000 -0.4524 0.01185 0.00399 -0.0026 1.0000 0.2065
-3.750 -0.4250 0.01153 0.00378 -0.0025 1.0000 0.2315
-3.500 -0.3975 0.01125 0.00360 -0.0024 1.0000 0.2560
-3.250 -0.3700 0.01100 0.00345 -0.0022 1.0000 0.2813
-3.000 -0.3425 0.01076 0.00332 -0.0021 1.0000 0.3062
-2.750 -0.3150 0.01056 0.00322 -0.0019 1.0000 0.3307
-2.500 -0.2875 0.01037 0.00313 -0.0017 1.0000 0.3526
-2.250 -0.2600 0.01021 0.00305 -0.0015 1.0000 0.3741
-2.000 -0.2325 0.01007 0.00298 -0.0012 1.0000 0.3948
-1.750 -0.2053 0.00991 0.00293 -0.0010 1.0000 0.4137
-1.500 -0.1672 0.00978 0.00289 -0.0030 0.9595 0.4344
-1.250 -0.1286 0.00971 0.00284 -0.0048 0.8908 0.4560
-1.000 -0.1016 0.00975 0.00277 -0.0038 0.8094 0.4757
-0.750 -0.0778 0.00987 0.00270 -0.0022 0.7320 0.4954
-0.500 -0.0528 0.00998 0.00265 -0.0012 0.6667 0.5177
0.250 0.0265 0.01005 0.00262 0.0005 0.5444 0.6169
0.500 0.0528 0.00998 0.00265 0.0012 0.5177 0.6669
0.750 0.0778 0.00987 0.00270 0.0022 0.4954 0.7320
1.000 0.1016 0.00975 0.00277 0.0038 0.4757 0.8094
1.250 0.1286 0.00971 0.00284 0.0048 0.4560 0.8907
1.500 0.1672 0.00978 0.00289 0.0030 0.4344 0.9595
1.750 0.2053 0.00991 0.00293 0.0010 0.4137 1.0000
2.250 0.2600 0.01021 0.00305 0.0015 0.3741 1.0000
2.500 0.2875 0.01037 0.00313 0.0017 0.3526 1.0000
2.750 0.3150 0.01056 0.00322 0.0019 0.3307 1.0000
3.000 0.3425 0.01076 0.00332 0.0021 0.3062 1.0000
3.250 0.3700 0.01100 0.00345 0.0022 0.2813 1.0000
3.500 0.3975 0.01125 0.00360 0.0024 0.2560 1.0000
3.750 0.4250 0.01153 0.00378 0.0025 0.2315 1.0000
4.000 0.4523 0.01185 0.00399 0.0026 0.2065 1.0000
4.250 0.4797 0.01218 0.00423 0.0028 0.1831 1.0000
4.500 0.5070 0.01255 0.00449 0.0029 0.1611 1.0000
4.750 0.5343 0.01293 0.00480 0.0030 0.1418 1.0000
5.000 0.5615 0.01332 0.00513 0.0031 0.1245 1.0000
5.250 0.5886 0.01374 0.00549 0.0033 0.1098 1.0000
5.500 0.6156 0.01418 0.00589 0.0034 0.0972 1.0000
5.750 0.6425 0.01464 0.00632 0.0036 0.0871 1.0000
6.000 0.6692 0.01514 0.00678 0.0037 0.0784 1.0000
6.250 0.6960 0.01560 0.00728 0.0039 0.0715 1.0000
6.500 0.7222 0.01616 0.00782 0.0041 0.0657 1.0000
6.750 0.7487 0.01667 0.00837 0.0044 0.0607 1.0000
7.000 0.7744 0.01733 0.00901 0.0046 0.0566 1.0000
7.250 0.8005 0.01787 0.00964 0.0049 0.0529 1.0000
7.500 0.8260 0.01850 0.01029 0.0051 0.0496 1.0000
7.750 0.8509 0.01924 0.01108 0.0054 0.0469 1.0000
8.000 0.8761 0.01990 0.01184 0.0058 0.0442 1.0000
8.250 0.9008 0.02061 0.01258 0.0061 0.0419 1.0000
8.500 0.9245 0.02150 0.01351 0.0065 0.0401 1.0000
8.750 0.9485 0.02232 0.01447 0.0069 0.0383 1.0000
9.000 0.9721 0.02315 0.01538 0.0073 0.0366 1.0000
9.250 0.9950 0.02402 0.01628 0.0077 0.0351 1.0000
9.500 1.0169 0.02510 0.01744 0.0082 0.0338 1.0000
9.750 1.0388 0.02615 0.01868 0.0087 0.0325 1.0000
10.000 1.0598 0.02729 0.01994 0.0093 0.0314 1.0000
10.250 1.0802 0.02843 0.02119 0.0098 0.0305 1.0000
10.500 1.0997 0.02962 0.02245 0.0104 0.0297 1.0000
10.750 1.1175 0.03102 0.02391 0.0110 0.0290 1.0000
11.000 1.1339 0.03263 0.02575 0.0118 0.0283 1.0000
11.250 1.1487 0.03435 0.02771 0.0125 0.0275 1.0000
11.500 1.1618 0.03612 0.02970 0.0133 0.0268 1.0000
11.750 1.1731 0.03790 0.03167 0.0140 0.0261 1.0000
12.000 1.1820 0.03976 0.03369 0.0147 0.0256 1.0000
12.250 1.1876 0.04177 0.03584 0.0154 0.0252 1.0000
12.500 1.1869 0.04403 0.03823 0.0164 0.0249 1.0000
12.750 1.1840 0.04690 0.04124 0.0160 0.0247 1.0000
13.000 1.1792 0.05060 0.04509 0.0140 0.0245 1.0000
13.250 1.1718 0.05531 0.04996 0.0107 0.0243 1.0000
13.500 1.1610 0.06102 0.05585 0.0064 0.0242 1.0000
13.750 1.1435 0.06826 0.06331 0.0008 0.0242 1.0000
14.000 1.1209 0.07660 0.07186 -0.0054 0.0242 1.0000
14.250 1.0934 0.08602 0.08147 -0.0119 0.0242 1.0000
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