BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il) Reynolds number: 1,000,000 Max Cl/Cd: 74.78 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-b540ols-il-1000000.txt Download as CSV file: xf-b540ols-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.1950 0.12715 0.12480 0.0383 1.0000 0.0151
-17.500 -1.2232 0.11730 0.11483 0.0329 1.0000 0.0151
-17.250 -1.2506 0.10791 0.10531 0.0277 1.0000 0.0151
-17.000 -1.2778 0.09888 0.09616 0.0228 1.0000 0.0151
-16.750 -1.3071 0.08994 0.08709 0.0179 1.0000 0.0150
-16.500 -1.3364 0.08131 0.07833 0.0133 1.0000 0.0150
-16.250 -1.3646 0.07296 0.06984 0.0087 1.0000 0.0150
-16.000 -1.3906 0.06495 0.06170 0.0040 1.0000 0.0150
-15.750 -1.4125 0.05743 0.05404 -0.0006 1.0000 0.0150
-15.500 -1.4284 0.05050 0.04695 -0.0055 1.0000 0.0150
-15.250 -1.4380 0.04429 0.04059 -0.0105 1.0000 0.0151
-15.000 -1.4436 0.03919 0.03533 -0.0149 1.0000 0.0152
-14.750 -1.4471 0.03554 0.03153 -0.0170 1.0000 0.0153
-14.500 -1.4488 0.03305 0.02892 -0.0168 1.0000 0.0155
-14.250 -1.4481 0.03130 0.02706 -0.0151 1.0000 0.0156
-14.000 -1.4394 0.02983 0.02547 -0.0139 1.0000 0.0158
-13.750 -1.4266 0.02855 0.02410 -0.0130 1.0000 0.0161
-13.500 -1.4111 0.02746 0.02289 -0.0121 1.0000 0.0163
-13.250 -1.3936 0.02649 0.02183 -0.0114 1.0000 0.0166
-13.000 -1.3747 0.02562 0.02087 -0.0107 1.0000 0.0167
-12.750 -1.3623 0.02387 0.01897 -0.0096 1.0000 0.0171
-12.500 -1.3454 0.02255 0.01758 -0.0087 1.0000 0.0175
-12.250 -1.3250 0.02165 0.01661 -0.0081 1.0000 0.0179
-12.000 -1.3030 0.02089 0.01581 -0.0076 1.0000 0.0183
-11.750 -1.2804 0.02019 0.01504 -0.0071 1.0000 0.0187
-11.500 -1.2573 0.01952 0.01431 -0.0066 1.0000 0.0191
-11.250 -1.2337 0.01888 0.01360 -0.0062 1.0000 0.0195
-11.000 -1.2095 0.01830 0.01295 -0.0058 1.0000 0.0199
-10.750 -1.1845 0.01782 0.01240 -0.0055 1.0000 0.0202
-10.500 -1.1628 0.01672 0.01123 -0.0049 1.0000 0.0212
-10.250 -1.1378 0.01616 0.01065 -0.0046 1.0000 0.0219
-10.000 -1.1123 0.01568 0.01014 -0.0043 1.0000 0.0227
-9.750 -1.0865 0.01523 0.00963 -0.0040 1.0000 0.0234
-9.500 -1.0602 0.01483 0.00918 -0.0038 1.0000 0.0240
-9.250 -1.0351 0.01416 0.00846 -0.0035 1.0000 0.0251
-9.000 -1.0090 0.01365 0.00794 -0.0032 1.0000 0.0262
-8.750 -0.9823 0.01327 0.00754 -0.0031 1.0000 0.0274
-8.500 -0.9553 0.01294 0.00717 -0.0029 1.0000 0.0284
-8.250 -0.9288 0.01246 0.00665 -0.0027 1.0000 0.0300
-8.000 -0.9019 0.01206 0.00627 -0.0025 1.0000 0.0318
-7.750 -0.8744 0.01177 0.00596 -0.0024 1.0000 0.0334
-7.500 -0.8472 0.01139 0.00555 -0.0022 1.0000 0.0354
-7.250 -0.8198 0.01103 0.00520 -0.0021 1.0000 0.0379
-7.000 -0.7920 0.01077 0.00493 -0.0020 1.0000 0.0400
-6.750 -0.7645 0.01040 0.00457 -0.0019 1.0000 0.0434
-6.500 -0.7366 0.01014 0.00431 -0.0018 1.0000 0.0467
-6.250 -0.7088 0.00982 0.00401 -0.0017 1.0000 0.0511
-6.000 -0.6808 0.00957 0.00377 -0.0016 1.0000 0.0553
-5.750 -0.6528 0.00926 0.00351 -0.0016 1.0000 0.0619
-5.500 -0.6247 0.00900 0.00328 -0.0015 1.0000 0.0691
-5.250 -0.5965 0.00875 0.00307 -0.0014 1.0000 0.0771
-5.000 -0.5684 0.00849 0.00286 -0.0014 1.0000 0.0879
-4.750 -0.5402 0.00822 0.00267 -0.0014 1.0000 0.1012
-4.500 -0.5120 0.00795 0.00248 -0.0013 1.0000 0.1168
-4.250 -0.4837 0.00768 0.00232 -0.0013 1.0000 0.1350
-4.000 -0.4554 0.00744 0.00217 -0.0013 1.0000 0.1537
-3.750 -0.4271 0.00721 0.00202 -0.0013 1.0000 0.1741
-3.500 -0.3988 0.00698 0.00190 -0.0012 1.0000 0.1961
-3.250 -0.3704 0.00678 0.00179 -0.0012 1.0000 0.2185
-3.000 -0.3421 0.00657 0.00169 -0.0012 1.0000 0.2419
-2.750 -0.3137 0.00640 0.00161 -0.0011 1.0000 0.2643
-2.500 -0.2844 0.00622 0.00155 -0.0013 0.9968 0.2876
-2.250 -0.2466 0.00612 0.00152 -0.0032 0.9548 0.3124
-2.000 -0.2231 0.00617 0.00148 -0.0017 0.8818 0.3325
-1.750 -0.1985 0.00632 0.00142 -0.0006 0.7986 0.3522
-1.500 -0.1716 0.00651 0.00136 -0.0001 0.7127 0.3712
-1.250 -0.1436 0.00667 0.00133 0.0000 0.6397 0.3884
-1.000 -0.1151 0.00678 0.00129 0.0000 0.5848 0.4032
-0.750 -0.0864 0.00685 0.00127 0.0000 0.5445 0.4189
-0.500 -0.0576 0.00689 0.00126 0.0000 0.5137 0.4351
-0.250 -0.0288 0.00692 0.00125 0.0000 0.4890 0.4511
0.000 0.0001 0.00693 0.00125 0.0000 0.4681 0.4680
0.250 0.0289 0.00692 0.00125 0.0000 0.4510 0.4892
0.500 0.0577 0.00689 0.00126 0.0000 0.4352 0.5137
0.750 0.0865 0.00685 0.00127 -0.0001 0.4188 0.5445
1.000 0.1152 0.00678 0.00129 -0.0001 0.4031 0.5848
1.250 0.1437 0.00667 0.00133 0.0000 0.3884 0.6396
1.500 0.1717 0.00651 0.00136 0.0001 0.3712 0.7130
1.750 0.1986 0.00632 0.00142 0.0005 0.3522 0.7987
2.000 0.2232 0.00617 0.00148 0.0017 0.3327 0.8822
2.250 0.2467 0.00612 0.00151 0.0032 0.3125 0.9550
2.500 0.2844 0.00622 0.00155 0.0013 0.2876 0.9967
3.000 0.3422 0.00657 0.00169 0.0012 0.2421 1.0000
3.250 0.3705 0.00678 0.00179 0.0012 0.2184 1.0000
3.500 0.3989 0.00698 0.00190 0.0012 0.1961 1.0000
3.750 0.4272 0.00722 0.00203 0.0012 0.1739 1.0000
4.000 0.4555 0.00744 0.00217 0.0013 0.1537 1.0000
4.250 0.4838 0.00768 0.00232 0.0013 0.1350 1.0000
4.500 0.5121 0.00795 0.00248 0.0013 0.1168 1.0000
4.750 0.5403 0.00822 0.00267 0.0013 0.1012 1.0000
5.000 0.5685 0.00849 0.00286 0.0014 0.0879 1.0000
5.250 0.5966 0.00875 0.00307 0.0014 0.0772 1.0000
5.500 0.6248 0.00900 0.00328 0.0015 0.0690 1.0000
5.750 0.6529 0.00926 0.00351 0.0015 0.0618 1.0000
6.000 0.6809 0.00957 0.00377 0.0016 0.0553 1.0000
6.250 0.7089 0.00982 0.00401 0.0017 0.0511 1.0000
6.500 0.7367 0.01014 0.00431 0.0018 0.0467 1.0000
6.750 0.7646 0.01040 0.00457 0.0019 0.0434 1.0000
7.000 0.7921 0.01077 0.00493 0.0020 0.0400 1.0000
7.250 0.8199 0.01103 0.00520 0.0021 0.0379 1.0000
7.500 0.8473 0.01140 0.00555 0.0022 0.0354 1.0000
7.750 0.8745 0.01177 0.00596 0.0024 0.0334 1.0000
8.000 0.9019 0.01206 0.00626 0.0025 0.0318 1.0000
8.250 0.9289 0.01246 0.00665 0.0026 0.0300 1.0000
8.500 0.9554 0.01294 0.00717 0.0028 0.0284 1.0000
8.750 0.9824 0.01327 0.00754 0.0030 0.0274 1.0000
9.000 1.0092 0.01365 0.00794 0.0032 0.0262 1.0000
9.250 1.0352 0.01416 0.00846 0.0034 0.0251 1.0000
9.500 1.0604 0.01483 0.00918 0.0038 0.0240 1.0000
9.750 1.0866 0.01523 0.00963 0.0040 0.0234 1.0000
10.000 1.1124 0.01569 0.01014 0.0043 0.0227 1.0000
10.250 1.1380 0.01616 0.01065 0.0046 0.0219 1.0000
10.500 1.1629 0.01672 0.01123 0.0049 0.0212 1.0000
10.750 1.1846 0.01782 0.01240 0.0054 0.0202 1.0000
11.000 1.2096 0.01830 0.01295 0.0058 0.0199 1.0000
11.250 1.2338 0.01888 0.01360 0.0062 0.0195 1.0000
11.500 1.2574 0.01952 0.01431 0.0066 0.0191 1.0000
11.750 1.2806 0.02019 0.01505 0.0071 0.0187 1.0000
12.000 1.3032 0.02090 0.01581 0.0075 0.0183 1.0000
12.250 1.3252 0.02165 0.01661 0.0081 0.0179 1.0000
12.500 1.3456 0.02255 0.01758 0.0087 0.0175 1.0000
12.750 1.3625 0.02387 0.01898 0.0095 0.0171 1.0000
13.000 1.3750 0.02562 0.02086 0.0106 0.0167 1.0000
13.250 1.3940 0.02648 0.02182 0.0113 0.0165 1.0000
13.500 1.4116 0.02744 0.02287 0.0121 0.0163 1.0000
13.750 1.4271 0.02854 0.02408 0.0129 0.0161 1.0000
14.000 1.4400 0.02982 0.02546 0.0139 0.0158 1.0000
14.250 1.4487 0.03130 0.02705 0.0150 0.0156 1.0000
14.500 1.4498 0.03303 0.02890 0.0167 0.0155 1.0000
14.750 1.4481 0.03551 0.03151 0.0169 0.0153 1.0000
15.000 1.4447 0.03915 0.03529 0.0147 0.0152 1.0000
15.250 1.4393 0.04424 0.04053 0.0104 0.0151 1.0000
15.500 1.4300 0.05040 0.04685 0.0053 0.0150 1.0000
15.750 1.4143 0.05735 0.05395 0.0004 0.0150 1.0000
16.000 1.3926 0.06486 0.06161 -0.0042 0.0150 1.0000
16.250 1.3665 0.07289 0.06978 -0.0089 0.0150 1.0000
16.500 1.3383 0.08126 0.07828 -0.0135 0.0150 1.0000
16.750 1.3091 0.08989 0.08704 -0.0182 0.0150 1.0000
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Polar data table (+)
Polar graphs
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