USA 46 AIRFOIL (usa46-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 46 AIRFOIL (usa46-il) Reynolds number: 50,000 Max Cl/Cd: 38.3 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa46-il-50000.txt Download as CSV file: xf-usa46-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: USA 46 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4826 0.10021 0.09332 -0.0029 1.0000 0.2181
-7.750 -0.4800 0.09668 0.08986 -0.0034 1.0000 0.2242
-7.500 -0.4858 0.09475 0.08804 -0.0043 1.0000 0.2338
-7.250 -0.4740 0.09054 0.08384 -0.0033 1.0000 0.2454
-7.000 -0.4708 0.08741 0.08074 -0.0030 1.0000 0.2588
-6.750 -0.4700 0.08460 0.07801 -0.0034 1.0000 0.2751
-6.500 -0.4729 0.08218 0.07569 -0.0055 1.0000 0.2914
-6.250 -0.4617 0.07811 0.07165 -0.0035 1.0000 0.3082
-6.000 -0.4509 0.07466 0.06823 -0.0015 1.0000 0.3282
-5.750 -0.4462 0.07164 0.06527 -0.0006 1.0000 0.3524
-5.500 -0.4455 0.06963 0.06332 0.0008 1.0000 0.3910
-4.750 -0.3424 0.04019 0.03181 -0.0498 1.0000 0.1637
-4.500 -0.3193 0.03646 0.02785 -0.0503 1.0000 0.1678
-4.250 -0.2920 0.03327 0.02395 -0.0515 1.0000 0.1781
-4.000 -0.2677 0.03039 0.02089 -0.0514 1.0000 0.1845
-3.750 -0.2423 0.02815 0.01830 -0.0513 1.0000 0.1986
-3.500 -0.2166 0.02610 0.01588 -0.0511 1.0000 0.2133
-3.250 -0.1904 0.02418 0.01366 -0.0507 1.0000 0.2282
-3.000 -0.1661 0.02272 0.01210 -0.0501 1.0000 0.2548
-2.750 -0.1408 0.02124 0.01053 -0.0494 1.0000 0.2821
-2.500 -0.1173 0.02004 0.00938 -0.0484 1.0000 0.3223
-2.250 -0.0923 0.01894 0.00837 -0.0476 1.0000 0.3689
-2.000 -0.0676 0.01794 0.00763 -0.0468 1.0000 0.4289
-1.750 -0.0446 0.01683 0.00710 -0.0456 1.0000 0.5212
-1.500 -0.0256 0.01460 0.00637 -0.0410 1.0000 1.0000
-1.250 0.0024 0.01468 0.00580 -0.0415 1.0000 1.0000
-1.000 0.0269 0.01479 0.00552 -0.0413 1.0000 1.0000
-0.750 0.0505 0.01494 0.00539 -0.0409 1.0000 1.0000
-0.500 0.0735 0.01511 0.00536 -0.0406 1.0000 1.0000
-0.250 0.0959 0.01533 0.00539 -0.0401 1.0000 1.0000
0.000 0.1179 0.01558 0.00549 -0.0397 1.0000 1.0000
0.250 0.1393 0.01588 0.00567 -0.0393 1.0000 1.0000
0.500 0.1601 0.01622 0.00593 -0.0388 1.0000 1.0000
0.750 0.1802 0.01663 0.00627 -0.0385 1.0000 1.0000
1.000 0.1996 0.01710 0.00669 -0.0381 1.0000 1.0000
1.250 0.2183 0.01764 0.00721 -0.0378 1.0000 1.0000
1.500 0.2363 0.01827 0.00783 -0.0376 1.0000 1.0000
1.750 0.2535 0.01899 0.00854 -0.0375 1.0000 1.0000
2.000 0.2701 0.01980 0.00937 -0.0376 1.0000 1.0000
2.250 0.3270 0.02094 0.01067 -0.0450 0.9792 1.0000
2.500 0.3933 0.02185 0.01176 -0.0534 0.9512 1.0000
2.750 0.4576 0.02242 0.01258 -0.0606 0.9218 1.0000
3.000 0.5241 0.02264 0.01317 -0.0674 0.8914 1.0000
3.250 0.5887 0.02252 0.01342 -0.0727 0.8600 1.0000
3.500 0.6374 0.02239 0.01366 -0.0746 0.8253 1.0000
3.750 0.6791 0.02223 0.01377 -0.0747 0.7896 1.0000
4.000 0.7108 0.02230 0.01405 -0.0732 0.7517 1.0000
4.250 0.7402 0.02236 0.01428 -0.0709 0.7144 1.0000
4.500 0.7662 0.02235 0.01443 -0.0679 0.6749 1.0000
4.750 0.7876 0.02234 0.01449 -0.0641 0.6287 1.0000
5.000 0.8040 0.02170 0.01369 -0.0584 0.5648 1.0000
5.250 0.8127 0.02122 0.01289 -0.0523 0.4719 1.0000
5.500 0.8112 0.02290 0.01322 -0.0459 0.2492 1.0000
5.750 0.8247 0.02629 0.01536 -0.0436 0.1411 1.0000
6.000 0.8483 0.02880 0.01772 -0.0420 0.1197 1.0000
6.250 0.8752 0.03129 0.02016 -0.0409 0.1060 1.0000
6.500 0.9027 0.03387 0.02295 -0.0400 0.0970 1.0000
6.750 0.9302 0.03686 0.02613 -0.0391 0.0932 1.0000
7.000 0.9559 0.04053 0.03005 -0.0383 0.0914 1.0000
7.250 0.9781 0.04464 0.03455 -0.0373 0.0908 1.0000
7.500 0.9954 0.04835 0.03885 -0.0358 0.0902 1.0000
7.750 1.0088 0.05238 0.04355 -0.0344 0.0897 1.0000
8.000 1.0206 0.05696 0.04858 -0.0333 0.0900 1.0000
8.250 1.0189 0.06186 0.05441 -0.0318 0.0939 1.0000
8.500 1.0098 0.06814 0.06127 -0.0315 0.0986 1.0000
8.750 1.0114 0.07384 0.06714 -0.0314 0.1024 1.0000
9.000 0.9864 0.08022 0.07393 -0.0328 0.1076 1.0000
9.250 0.9544 0.08708 0.08086 -0.0354 0.1123 1.0000
9.500 0.9254 0.09578 0.08958 -0.0417 0.1217 1.0000
9.750 0.8992 0.10784 0.10155 -0.0517 0.1417 1.0000
10.000 0.7681 0.11079 0.10483 -0.0486 0.1406 1.0000
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Polar data table (+)
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