BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BELL 540 AIRFOIL (MODIFIED NACA 0012) (b540ols-il) Reynolds number: 100,000 Max Cl/Cd: 34.11 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-b540ols-il-100000-n5.txt Download as CSV file: xf-b540ols-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.8884 0.09802 0.09253 0.0187 1.0000 0.0406
-12.000 -0.9426 0.08118 0.07557 0.0064 1.0000 0.0398
-11.750 -0.9841 0.06849 0.06264 -0.0049 1.0000 0.0393
-11.500 -1.0136 0.06028 0.05414 -0.0121 1.0000 0.0391
-11.250 -1.0357 0.05511 0.04868 -0.0139 1.0000 0.0392
-11.000 -1.0483 0.05069 0.04386 -0.0141 1.0000 0.0397
-10.750 -1.0532 0.04662 0.03927 -0.0139 1.0000 0.0405
-10.500 -1.0435 0.04417 0.03667 -0.0134 1.0000 0.0415
-10.250 -1.0297 0.04230 0.03470 -0.0129 1.0000 0.0426
-10.000 -1.0157 0.04021 0.03241 -0.0124 1.0000 0.0438
-9.750 -1.0009 0.03793 0.02983 -0.0118 1.0000 0.0451
-9.500 -0.9846 0.03567 0.02722 -0.0112 1.0000 0.0467
-9.250 -0.9664 0.03367 0.02490 -0.0106 1.0000 0.0486
-9.000 -0.9459 0.03232 0.02356 -0.0102 1.0000 0.0505
-8.750 -0.9248 0.03094 0.02205 -0.0097 1.0000 0.0527
-8.500 -0.9031 0.02942 0.02030 -0.0092 1.0000 0.0551
-8.250 -0.8810 0.02801 0.01872 -0.0087 1.0000 0.0578
-8.000 -0.8583 0.02693 0.01764 -0.0083 1.0000 0.0608
-7.750 -0.8348 0.02580 0.01636 -0.0078 1.0000 0.0644
-7.500 -0.8113 0.02463 0.01510 -0.0073 1.0000 0.0680
-7.250 -0.7875 0.02370 0.01416 -0.0069 1.0000 0.0725
-7.000 -0.7627 0.02279 0.01308 -0.0064 1.0000 0.0778
-6.750 -0.7387 0.02185 0.01219 -0.0061 1.0000 0.0835
-6.500 -0.7136 0.02102 0.01129 -0.0057 1.0000 0.0907
-6.250 -0.6886 0.02022 0.01051 -0.0054 1.0000 0.0990
-6.000 -0.6634 0.01945 0.00975 -0.0051 1.0000 0.1089
-5.750 -0.6377 0.01874 0.00905 -0.0048 1.0000 0.1208
-5.500 -0.6119 0.01807 0.00842 -0.0046 1.0000 0.1355
-5.250 -0.5858 0.01745 0.00784 -0.0043 1.0000 0.1531
-5.000 -0.5595 0.01688 0.00732 -0.0041 1.0000 0.1742
-4.750 -0.5333 0.01633 0.00689 -0.0039 1.0000 0.1976
-4.500 -0.5067 0.01586 0.00649 -0.0037 1.0000 0.2232
-4.250 -0.4800 0.01544 0.00616 -0.0035 1.0000 0.2507
-4.000 -0.4533 0.01506 0.00589 -0.0032 1.0000 0.2784
-3.750 -0.4266 0.01472 0.00564 -0.0030 1.0000 0.3059
-3.500 -0.3996 0.01444 0.00543 -0.0027 1.0000 0.3326
-3.250 -0.3726 0.01418 0.00525 -0.0024 1.0000 0.3580
-3.000 -0.3456 0.01394 0.00507 -0.0021 1.0000 0.3824
-2.750 -0.3187 0.01370 0.00491 -0.0018 1.0000 0.4061
-2.500 -0.2917 0.01347 0.00474 -0.0014 1.0000 0.4288
-2.250 -0.2650 0.01322 0.00460 -0.0010 1.0000 0.4503
-2.000 -0.2382 0.01299 0.00447 -0.0007 1.0000 0.4726
-1.750 -0.2116 0.01276 0.00437 -0.0003 1.0000 0.4956
-1.500 -0.1852 0.01252 0.00428 0.0002 1.0000 0.5194
-1.250 -0.1588 0.01230 0.00422 0.0007 1.0000 0.5455
-1.000 -0.1331 0.01208 0.00419 0.0012 1.0000 0.5750
-0.750 -0.1072 0.01185 0.00419 0.0018 0.9987 0.6101
-0.500 -0.0648 0.01164 0.00423 -0.0008 0.9427 0.6598
-0.250 -0.0270 0.01146 0.00426 -0.0018 0.8688 0.7207
0.000 0.0000 0.01140 0.00426 0.0000 0.7907 0.7907
0.250 0.0270 0.01146 0.00426 0.0018 0.7207 0.8689
0.500 0.0648 0.01164 0.00423 0.0008 0.6598 0.9427
0.750 0.1071 0.01185 0.00419 -0.0018 0.6102 0.9987
1.000 0.1331 0.01208 0.00419 -0.0012 0.5750 1.0000
1.250 0.1588 0.01230 0.00422 -0.0006 0.5455 1.0000
1.500 0.1852 0.01252 0.00428 -0.0002 0.5194 1.0000
1.750 0.2116 0.01276 0.00437 0.0003 0.4956 1.0000
2.000 0.2382 0.01299 0.00447 0.0007 0.4726 1.0000
2.250 0.2649 0.01322 0.00460 0.0011 0.4503 1.0000
2.500 0.2916 0.01347 0.00474 0.0014 0.4288 1.0000
2.750 0.3186 0.01370 0.00491 0.0018 0.4061 1.0000
3.000 0.3456 0.01394 0.00507 0.0021 0.3825 1.0000
3.250 0.3726 0.01418 0.00525 0.0024 0.3581 1.0000
3.500 0.3996 0.01444 0.00543 0.0027 0.3326 1.0000
3.750 0.4265 0.01472 0.00564 0.0030 0.3059 1.0000
4.000 0.4533 0.01506 0.00589 0.0032 0.2784 1.0000
4.250 0.4800 0.01544 0.00616 0.0035 0.2507 1.0000
4.500 0.5067 0.01586 0.00649 0.0037 0.2232 1.0000
4.750 0.5333 0.01633 0.00689 0.0039 0.1976 1.0000
5.000 0.5595 0.01688 0.00732 0.0041 0.1742 1.0000
5.250 0.5858 0.01745 0.00784 0.0043 0.1532 1.0000
5.500 0.6119 0.01807 0.00842 0.0046 0.1355 1.0000
5.750 0.6377 0.01874 0.00905 0.0048 0.1208 1.0000
6.000 0.6634 0.01945 0.00975 0.0051 0.1089 1.0000
6.250 0.6887 0.02022 0.01051 0.0054 0.0990 1.0000
6.500 0.7136 0.02102 0.01129 0.0057 0.0907 1.0000
6.750 0.7387 0.02185 0.01219 0.0061 0.0835 1.0000
7.000 0.7627 0.02279 0.01308 0.0064 0.0778 1.0000
7.250 0.7875 0.02370 0.01416 0.0069 0.0725 1.0000
7.500 0.8114 0.02463 0.01510 0.0073 0.0679 1.0000
7.750 0.8349 0.02580 0.01636 0.0078 0.0644 1.0000
8.000 0.8583 0.02693 0.01764 0.0082 0.0608 1.0000
8.250 0.8810 0.02801 0.01872 0.0086 0.0578 1.0000
8.500 0.9032 0.02942 0.02030 0.0092 0.0551 1.0000
8.750 0.9249 0.03094 0.02205 0.0097 0.0527 1.0000
9.000 0.9460 0.03232 0.02356 0.0102 0.0505 1.0000
9.250 0.9665 0.03367 0.02490 0.0106 0.0486 1.0000
9.500 0.9847 0.03567 0.02723 0.0112 0.0467 1.0000
9.750 1.0011 0.03793 0.02983 0.0118 0.0451 1.0000
10.000 1.0159 0.04022 0.03242 0.0124 0.0438 1.0000
10.250 1.0299 0.04231 0.03471 0.0129 0.0426 1.0000
10.500 1.0437 0.04417 0.03667 0.0134 0.0415 1.0000
10.750 1.0534 0.04664 0.03929 0.0139 0.0405 1.0000
11.000 1.0485 0.05072 0.04388 0.0141 0.0397 1.0000
11.250 1.0359 0.05515 0.04872 0.0138 0.0392 1.0000
11.500 1.0139 0.06033 0.05420 0.0120 0.0391 1.0000
11.750 0.9843 0.06861 0.06277 0.0047 0.0392 1.0000
12.000 0.9425 0.08142 0.07582 -0.0067 0.0398 1.0000
12.250 0.8879 0.09842 0.09294 -0.0192 0.0406 1.0000
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Polar data table (+)
Polar graphs
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