NASA/LANGLEY RC-08(B)3 AIRFOIL (rc08b3-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-08(B)3 AIRFOIL (rc08b3-il) Reynolds number: 200,000 Max Cl/Cd: 57.7 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rc08b3-il-200000.txt Download as CSV file: xf-rc08b3-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC-08(B)3 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5988 0.09813 0.09463 -0.0133 1.0000 0.0453
-9.000 -0.6053 0.09292 0.08941 -0.0192 1.0000 0.0454
-8.750 -0.6119 0.08865 0.08507 -0.0217 1.0000 0.0455
-8.500 -0.6157 0.08440 0.08070 -0.0236 1.0000 0.0456
-8.250 -0.6132 0.07752 0.07400 -0.0220 1.0000 0.0470
-8.000 -0.6064 0.07454 0.07101 -0.0211 1.0000 0.0481
-7.750 -0.6013 0.07114 0.06759 -0.0214 1.0000 0.0493
-7.500 -0.5965 0.06740 0.06378 -0.0222 1.0000 0.0509
-7.250 -0.5912 0.06343 0.05970 -0.0230 1.0000 0.0531
-7.000 -0.5876 0.06102 0.05664 -0.0236 1.0000 0.0579
-6.750 -0.5863 0.05403 0.04964 -0.0232 1.0000 0.0594
-6.500 -0.5735 0.05116 0.04687 -0.0223 1.0000 0.0611
-6.250 -0.5623 0.04863 0.04429 -0.0209 1.0000 0.0634
-6.000 -0.5524 0.04602 0.04151 -0.0191 1.0000 0.0670
-5.750 -0.5500 0.04304 0.03796 -0.0156 1.0000 0.0728
-5.500 -0.5386 0.04018 0.03516 -0.0140 1.0000 0.0745
-5.250 -0.5274 0.03816 0.03308 -0.0117 1.0000 0.0773
-5.000 -0.5204 0.03667 0.03105 -0.0081 1.0000 0.0867
-4.750 -0.5024 0.02105 0.01597 -0.0051 1.0000 0.0882
-4.500 -0.4870 0.02970 0.02312 -0.0015 1.0000 0.0576
-4.250 -0.4708 0.02434 0.01706 0.0015 1.0000 0.0467
-4.000 -0.4506 0.02371 0.01623 0.0034 1.0000 0.0457
-3.750 -0.4291 0.02090 0.01319 0.0046 1.0000 0.0442
-3.500 -0.4064 0.01927 0.01132 0.0058 1.0000 0.0439
-3.250 -0.3832 0.01805 0.00991 0.0068 1.0000 0.0442
-3.000 -0.3598 0.01712 0.00886 0.0078 1.0000 0.0449
-2.750 -0.3358 0.01597 0.00765 0.0085 1.0000 0.0467
-2.500 -0.3133 0.01519 0.00693 0.0093 1.0000 0.0510
-2.250 -0.2875 0.01460 0.00632 0.0095 0.9993 0.0551
-2.000 -0.2505 0.01377 0.00552 0.0075 0.9957 0.0640
-1.750 -0.2151 0.01270 0.00484 0.0056 0.9920 0.1341
-1.500 -0.0507 0.01027 0.00528 -0.0191 1.0000 1.0000
-1.250 -0.0471 0.01039 0.00533 -0.0150 1.0000 1.0000
-1.000 -0.0429 0.01054 0.00540 -0.0112 1.0000 1.0000
-0.750 -0.0087 0.01060 0.00536 -0.0131 0.9962 1.0000
-0.500 0.0368 0.01062 0.00529 -0.0172 0.9904 1.0000
-0.250 0.0844 0.01061 0.00521 -0.0217 0.9848 1.0000
0.000 0.1315 0.01055 0.00512 -0.0260 0.9779 1.0000
0.250 0.1824 0.01045 0.00499 -0.0310 0.9723 1.0000
0.500 0.2284 0.01033 0.00487 -0.0349 0.9645 1.0000
0.750 0.2745 0.01017 0.00472 -0.0387 0.9564 1.0000
1.000 0.3097 0.01005 0.00463 -0.0400 0.9437 1.0000
1.250 0.3392 0.00995 0.00455 -0.0401 0.9297 1.0000
1.500 0.3640 0.00987 0.00448 -0.0389 0.9144 1.0000
1.750 0.3858 0.00977 0.00439 -0.0371 0.8979 1.0000
2.000 0.4065 0.00969 0.00434 -0.0351 0.8791 1.0000
2.250 0.4276 0.00961 0.00427 -0.0331 0.8601 1.0000
2.500 0.4489 0.00951 0.00415 -0.0310 0.8397 1.0000
2.750 0.4702 0.00943 0.00406 -0.0291 0.8128 1.0000
3.000 0.4919 0.00937 0.00397 -0.0271 0.7800 1.0000
3.250 0.5140 0.00937 0.00390 -0.0254 0.7405 1.0000
3.500 0.5365 0.00946 0.00387 -0.0238 0.6921 1.0000
3.750 0.5585 0.00968 0.00387 -0.0222 0.6246 1.0000
4.000 0.5791 0.01016 0.00396 -0.0205 0.5274 1.0000
4.250 0.5983 0.01094 0.00420 -0.0189 0.4122 1.0000
4.750 0.6333 0.01332 0.00521 -0.0162 0.1485 1.0000
5.000 0.6511 0.01460 0.00605 -0.0147 0.0913 1.0000
5.250 0.6709 0.01548 0.00693 -0.0133 0.0751 1.0000
5.500 0.6895 0.01654 0.00791 -0.0117 0.0655 1.0000
5.750 0.7107 0.01720 0.00865 -0.0104 0.0592 1.0000
6.000 0.7301 0.01823 0.00965 -0.0090 0.0547 1.0000
6.250 0.7501 0.01970 0.01116 -0.0075 0.0518 1.0000
6.500 0.7720 0.02067 0.01227 -0.0062 0.0489 1.0000
6.750 0.7933 0.02162 0.01330 -0.0050 0.0456 1.0000
7.000 0.8146 0.02303 0.01476 -0.0039 0.0435 1.0000
7.250 0.8356 0.02574 0.01762 -0.0028 0.0419 1.0000
7.500 0.8547 0.02763 0.01984 -0.0012 0.0405 1.0000
7.750 0.8733 0.02902 0.02159 0.0006 0.0387 1.0000
8.000 0.8893 0.03154 0.02449 0.0027 0.0380 1.0000
8.250 0.9019 0.03468 0.02806 0.0051 0.0379 1.0000
8.500 0.9105 0.03814 0.03197 0.0079 0.0379 1.0000
8.750 0.9163 0.04149 0.03574 0.0107 0.0373 1.0000
9.000 0.9171 0.04558 0.04025 0.0137 0.0375 1.0000
9.250 0.9126 0.05063 0.04563 0.0165 0.0394 1.0000
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Polar data table (+)
Polar graphs
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