BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il) Reynolds number: 500,000 Max Cl/Cd: 62.1 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b540ols-il-500000-n5.txt Download as CSV file: xf-b540ols-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -1.0958 0.13959 0.13674 0.0457 1.0000 0.0156
-17.000 -1.1327 0.12699 0.12398 0.0386 1.0000 0.0156
-16.750 -1.1618 0.11670 0.11355 0.0330 1.0000 0.0156
-16.500 -1.1895 0.10700 0.10371 0.0277 1.0000 0.0156
-16.250 -1.2166 0.09790 0.09448 0.0227 1.0000 0.0156
-16.000 -1.2442 0.08916 0.08561 0.0179 1.0000 0.0156
-15.750 -1.2712 0.08068 0.07699 0.0133 1.0000 0.0156
-15.500 -1.2969 0.07252 0.06869 0.0086 1.0000 0.0156
-15.250 -1.3201 0.06475 0.06078 0.0040 1.0000 0.0156
-15.000 -1.3393 0.05747 0.05334 -0.0007 1.0000 0.0156
-14.750 -1.3533 0.05071 0.04641 -0.0057 1.0000 0.0157
-14.500 -1.3620 0.04469 0.04020 -0.0107 1.0000 0.0157
-14.250 -1.3675 0.03988 0.03520 -0.0146 1.0000 0.0159
-14.000 -1.3711 0.03652 0.03167 -0.0161 1.0000 0.0160
-13.750 -1.3720 0.03423 0.02923 -0.0154 1.0000 0.0161
-13.500 -1.3678 0.03251 0.02737 -0.0140 1.0000 0.0163
-13.250 -1.3570 0.03103 0.02574 -0.0131 1.0000 0.0165
-13.000 -1.3462 0.02944 0.02403 -0.0122 1.0000 0.0168
-12.750 -1.3325 0.02804 0.02255 -0.0114 1.0000 0.0172
-12.500 -1.3158 0.02687 0.02130 -0.0106 1.0000 0.0175
-12.250 -1.2975 0.02582 0.02016 -0.0100 1.0000 0.0178
-12.000 -1.2781 0.02485 0.01909 -0.0093 1.0000 0.0182
-11.750 -1.2578 0.02392 0.01806 -0.0088 1.0000 0.0186
-11.500 -1.2367 0.02304 0.01709 -0.0082 1.0000 0.0191
-11.250 -1.2150 0.02220 0.01614 -0.0077 1.0000 0.0195
-11.000 -1.1925 0.02143 0.01527 -0.0072 1.0000 0.0199
-10.750 -1.1702 0.02058 0.01434 -0.0067 1.0000 0.0205
-10.500 -1.1472 0.01979 0.01351 -0.0063 1.0000 0.0211
-10.250 -1.1233 0.01913 0.01279 -0.0059 1.0000 0.0217
-10.000 -1.0988 0.01853 0.01212 -0.0056 1.0000 0.0225
-9.750 -1.0739 0.01796 0.01149 -0.0053 1.0000 0.0234
-9.500 -1.0486 0.01744 0.01089 -0.0050 1.0000 0.0242
-9.250 -1.0238 0.01679 0.01020 -0.0047 1.0000 0.0252
-9.000 -0.9983 0.01626 0.00965 -0.0044 1.0000 0.0263
-8.750 -0.9723 0.01579 0.00912 -0.0041 1.0000 0.0274
-8.500 -0.9461 0.01534 0.00862 -0.0039 1.0000 0.0286
-8.250 -0.9200 0.01484 0.00808 -0.0037 1.0000 0.0299
-8.000 -0.8935 0.01439 0.00762 -0.0035 1.0000 0.0314
-7.750 -0.8668 0.01400 0.00719 -0.0033 1.0000 0.0332
-7.500 -0.8399 0.01361 0.00677 -0.0031 1.0000 0.0351
-7.250 -0.8130 0.01320 0.00637 -0.0030 1.0000 0.0375
-7.000 -0.7857 0.01286 0.00601 -0.0028 1.0000 0.0400
-6.750 -0.7585 0.01249 0.00563 -0.0027 1.0000 0.0429
-6.500 -0.7311 0.01216 0.00530 -0.0026 1.0000 0.0464
-6.250 -0.7036 0.01183 0.00497 -0.0024 1.0000 0.0499
-6.000 -0.6760 0.01151 0.00466 -0.0023 1.0000 0.0546
-5.750 -0.6484 0.01120 0.00437 -0.0022 1.0000 0.0597
-5.500 -0.6206 0.01092 0.00411 -0.0021 1.0000 0.0656
-5.250 -0.5928 0.01061 0.00384 -0.0020 1.0000 0.0728
-5.000 -0.5649 0.01034 0.00360 -0.0020 1.0000 0.0813
-4.750 -0.5370 0.01006 0.00337 -0.0019 1.0000 0.0914
-4.500 -0.5091 0.00979 0.00316 -0.0018 1.0000 0.1039
-4.250 -0.4811 0.00951 0.00296 -0.0017 1.0000 0.1180
-4.000 -0.4531 0.00924 0.00277 -0.0017 1.0000 0.1343
-3.750 -0.4251 0.00899 0.00260 -0.0016 1.0000 0.1518
-3.500 -0.3971 0.00875 0.00245 -0.0016 1.0000 0.1707
-3.250 -0.3691 0.00851 0.00232 -0.0015 1.0000 0.1909
-3.000 -0.3394 0.00829 0.00220 -0.0018 0.9912 0.2136
-2.750 -0.3024 0.00811 0.00211 -0.0036 0.9416 0.2391
-2.500 -0.2765 0.00810 0.00203 -0.0026 0.8656 0.2603
-2.250 -0.2529 0.00821 0.00193 -0.0012 0.7837 0.2814
-2.000 -0.2266 0.00829 0.00184 -0.0006 0.7141 0.3038
-1.750 -0.1992 0.00838 0.00177 -0.0003 0.6504 0.3251
-1.500 -0.1713 0.00848 0.00172 -0.0002 0.5963 0.3431
-1.250 -0.1430 0.00852 0.00168 -0.0001 0.5585 0.3634
-0.750 -0.0860 0.00858 0.00163 -0.0001 0.5000 0.3971
0.000 0.0000 0.00861 0.00159 0.0000 0.4437 0.4438
0.750 0.0860 0.00858 0.00163 0.0001 0.3970 0.5000
1.250 0.1430 0.00852 0.00168 0.0001 0.3634 0.5585
1.500 0.1713 0.00848 0.00172 0.0002 0.3432 0.5963
1.750 0.1992 0.00838 0.00178 0.0003 0.3250 0.6508
2.000 0.2266 0.00829 0.00184 0.0006 0.3038 0.7141
2.250 0.2529 0.00821 0.00193 0.0012 0.2815 0.7837
2.500 0.2766 0.00810 0.00203 0.0026 0.2603 0.8652
2.750 0.3024 0.00811 0.00211 0.0036 0.2389 0.9417
3.000 0.3393 0.00829 0.00220 0.0018 0.2137 0.9912
3.250 0.3691 0.00851 0.00232 0.0015 0.1909 1.0000
3.500 0.3971 0.00875 0.00245 0.0016 0.1707 1.0000
3.750 0.4251 0.00899 0.00260 0.0016 0.1518 1.0000
4.000 0.4531 0.00924 0.00277 0.0017 0.1343 1.0000
4.250 0.4811 0.00951 0.00296 0.0017 0.1181 1.0000
4.500 0.5090 0.00979 0.00316 0.0018 0.1038 1.0000
4.750 0.5370 0.01006 0.00337 0.0019 0.0914 1.0000
5.000 0.5649 0.01034 0.00360 0.0020 0.0813 1.0000
5.250 0.5928 0.01061 0.00384 0.0020 0.0728 1.0000
5.500 0.6206 0.01092 0.00411 0.0021 0.0656 1.0000
5.750 0.6484 0.01120 0.00437 0.0022 0.0597 1.0000
6.000 0.6760 0.01151 0.00466 0.0023 0.0546 1.0000
6.250 0.7036 0.01183 0.00497 0.0024 0.0499 1.0000
6.500 0.7311 0.01216 0.00530 0.0026 0.0464 1.0000
6.750 0.7585 0.01249 0.00563 0.0027 0.0429 1.0000
7.000 0.7857 0.01286 0.00601 0.0028 0.0400 1.0000
7.250 0.8130 0.01320 0.00637 0.0030 0.0375 1.0000
7.500 0.8399 0.01361 0.00677 0.0031 0.0351 1.0000
7.750 0.8668 0.01400 0.00719 0.0033 0.0332 1.0000
8.000 0.8936 0.01439 0.00762 0.0035 0.0314 1.0000
8.250 0.9200 0.01484 0.00808 0.0037 0.0299 1.0000
8.500 0.9461 0.01534 0.00862 0.0039 0.0286 1.0000
8.750 0.9724 0.01579 0.00912 0.0041 0.0274 1.0000
9.000 0.9984 0.01626 0.00965 0.0044 0.0263 1.0000
9.250 1.0239 0.01679 0.01021 0.0046 0.0252 1.0000
9.500 1.0487 0.01745 0.01089 0.0049 0.0242 1.0000
9.750 1.0740 0.01796 0.01149 0.0052 0.0234 1.0000
10.000 1.0989 0.01853 0.01212 0.0056 0.0225 1.0000
10.250 1.1234 0.01913 0.01279 0.0059 0.0217 1.0000
10.500 1.1473 0.01980 0.01351 0.0063 0.0211 1.0000
10.750 1.1703 0.02058 0.01434 0.0067 0.0205 1.0000
11.000 1.1927 0.02143 0.01527 0.0072 0.0199 1.0000
11.250 1.2152 0.02220 0.01615 0.0076 0.0195 1.0000
11.500 1.2369 0.02304 0.01709 0.0082 0.0191 1.0000
11.750 1.2580 0.02392 0.01807 0.0087 0.0186 1.0000
12.000 1.2783 0.02485 0.01909 0.0093 0.0182 1.0000
12.250 1.2977 0.02583 0.02016 0.0099 0.0178 1.0000
12.500 1.3161 0.02687 0.02130 0.0106 0.0175 1.0000
12.750 1.3328 0.02804 0.02255 0.0113 0.0172 1.0000
13.000 1.3466 0.02944 0.02404 0.0121 0.0168 1.0000
13.250 1.3575 0.03103 0.02574 0.0130 0.0165 1.0000
13.500 1.3684 0.03251 0.02736 0.0139 0.0163 1.0000
13.750 1.3728 0.03423 0.02923 0.0153 0.0161 1.0000
14.000 1.3719 0.03651 0.03166 0.0159 0.0160 1.0000
14.250 1.3685 0.03986 0.03519 0.0145 0.0159 1.0000
14.500 1.3632 0.04466 0.04017 0.0106 0.0157 1.0000
14.750 1.3546 0.05068 0.04638 0.0055 0.0157 1.0000
15.000 1.3407 0.05745 0.05332 0.0005 0.0156 1.0000
15.250 1.3216 0.06475 0.06078 -0.0042 0.0156 1.0000
15.500 1.2985 0.07251 0.06868 -0.0089 0.0156 1.0000
15.750 1.2729 0.08066 0.07697 -0.0135 0.0156 1.0000
16.000 1.2459 0.08916 0.08561 -0.0182 0.0156 1.0000
16.250 1.2182 0.09793 0.09452 -0.0230 0.0156 1.0000
16.500 1.1912 0.10703 0.10374 -0.0280 0.0156 1.0000
16.750 1.1633 0.11676 0.11362 -0.0333 0.0156 1.0000
17.000 1.1339 0.12712 0.12411 -0.0390 0.0156 1.0000
17.250 1.0966 0.13984 0.13699 -0.0461 0.0156 1.0000
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Polar data table (+)
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