LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il) Reynolds number: 200,000 Max Cl/Cd: 69.1 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141e-il-200000.txt Download as CSV file: xf-c141e-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL761.11 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5315 0.09104 0.08724 -0.0460 1.0000 0.0681
-9.250 -0.5662 0.08758 0.08378 -0.0456 1.0000 0.0682
-9.000 -0.6000 0.08432 0.08045 -0.0436 1.0000 0.0683
-8.750 -0.6262 0.08117 0.07717 -0.0413 1.0000 0.0684
-8.500 -0.6020 0.07625 0.07249 -0.0401 1.0000 0.0695
-8.250 -0.5984 0.07412 0.07041 -0.0376 1.0000 0.0701
-8.000 -0.6000 0.07185 0.06815 -0.0354 1.0000 0.0709
-7.750 -0.6033 0.06945 0.06573 -0.0333 1.0000 0.0720
-7.500 -0.6077 0.06676 0.06300 -0.0315 1.0000 0.0737
-7.250 -0.6350 0.06345 0.05903 -0.0298 1.0000 0.0793
-7.000 -0.6379 0.05764 0.05312 -0.0284 1.0000 0.0804
-6.750 -0.6271 0.05473 0.05034 -0.0271 1.0000 0.0815
-6.500 -0.6175 0.05252 0.04812 -0.0254 1.0000 0.0827
-6.250 -0.6264 0.03797 0.03214 -0.0225 1.0000 0.0578
-6.000 -0.6127 0.03463 0.02845 -0.0210 1.0000 0.0574
-5.750 -0.5961 0.03165 0.02502 -0.0196 1.0000 0.0577
-5.500 -0.5764 0.02902 0.02197 -0.0185 1.0000 0.0578
-5.250 -0.5549 0.02700 0.01952 -0.0175 1.0000 0.0584
-5.000 -0.5306 0.02506 0.01735 -0.0174 0.9996 0.0601
-4.750 -0.4962 0.02423 0.01651 -0.0192 0.9969 0.0625
-4.500 -0.4607 0.02311 0.01518 -0.0209 0.9947 0.0646
-4.250 -0.4266 0.02219 0.01401 -0.0221 0.9918 0.0672
-4.000 -0.3930 0.02109 0.01280 -0.0235 0.9889 0.0703
-3.750 -0.3573 0.02049 0.01220 -0.0254 0.9861 0.0737
-3.500 -0.3194 0.02006 0.01166 -0.0274 0.9839 0.0781
-3.250 -0.2896 0.01926 0.01089 -0.0281 0.9796 0.0829
-3.000 -0.2549 0.01886 0.01051 -0.0297 0.9759 0.0889
-2.750 -0.2183 0.01830 0.00999 -0.0317 0.9734 0.0965
-2.500 -0.1849 0.01806 0.00975 -0.0329 0.9694 0.1055
-2.250 -0.1538 0.01756 0.00937 -0.0339 0.9647 0.1162
-2.000 -0.1177 0.01719 0.00908 -0.0358 0.9614 0.1306
-1.750 -0.0787 0.01685 0.00884 -0.0384 0.9589 0.1512
-1.500 -0.0523 0.01641 0.00861 -0.0384 0.9527 0.1826
-1.250 -0.0261 0.01422 0.00862 -0.0389 0.9501 0.6841
-1.000 -0.0013 0.01396 0.00902 -0.0364 0.9467 0.8785
-0.750 0.0499 0.01424 0.00932 -0.0402 0.9457 0.9641
-0.500 0.1292 0.01456 0.00956 -0.0508 0.9478 1.0000
-0.250 0.1710 0.01456 0.00948 -0.0539 0.9447 1.0000
0.000 0.1924 0.01454 0.00941 -0.0530 0.9353 1.0000
0.250 0.2355 0.01446 0.00928 -0.0562 0.9313 1.0000
0.500 0.2716 0.01430 0.00909 -0.0577 0.9232 1.0000
0.750 0.3261 0.01387 0.00866 -0.0627 0.9171 1.0000
1.000 0.3964 0.01311 0.00790 -0.0704 0.9137 1.0000
1.250 0.4246 0.01274 0.00754 -0.0699 0.9018 1.0000
1.500 0.4607 0.01232 0.00713 -0.0710 0.8936 1.0000
1.750 0.4995 0.01170 0.00652 -0.0724 0.8837 1.0000
2.000 0.5276 0.01125 0.00608 -0.0716 0.8696 1.0000
2.250 0.5557 0.01085 0.00570 -0.0709 0.8545 1.0000
2.500 0.5835 0.01054 0.00538 -0.0702 0.8380 1.0000
2.750 0.6113 0.01031 0.00515 -0.0695 0.8199 1.0000
3.000 0.6351 0.01019 0.00501 -0.0681 0.7962 1.0000
3.250 0.6599 0.01008 0.00486 -0.0669 0.7670 1.0000
3.500 0.6831 0.01007 0.00475 -0.0653 0.7277 1.0000
3.750 0.7048 0.01020 0.00465 -0.0634 0.6696 1.0000
4.000 0.7192 0.01068 0.00465 -0.0601 0.5733 1.0000
4.250 0.7229 0.01166 0.00490 -0.0551 0.4383 1.0000
4.750 0.7372 0.01367 0.00582 -0.0475 0.2538 1.0000
5.000 0.7513 0.01444 0.00628 -0.0450 0.2057 1.0000
5.250 0.7676 0.01513 0.00675 -0.0429 0.1696 1.0000
5.500 0.7846 0.01581 0.00724 -0.0410 0.1450 1.0000
5.750 0.8034 0.01640 0.00774 -0.0393 0.1273 1.0000
6.000 0.8219 0.01705 0.00831 -0.0376 0.1137 1.0000
6.250 0.8397 0.01782 0.00899 -0.0359 0.1019 1.0000
6.500 0.8580 0.01861 0.00970 -0.0343 0.0918 1.0000
6.750 0.8777 0.01938 0.01049 -0.0328 0.0837 1.0000
7.000 0.8967 0.02050 0.01150 -0.0314 0.0777 1.0000
7.250 0.9183 0.02116 0.01224 -0.0302 0.0727 1.0000
7.500 0.9395 0.02218 0.01316 -0.0293 0.0685 1.0000
7.750 0.9628 0.02319 0.01424 -0.0286 0.0654 1.0000
8.000 0.9858 0.02408 0.01522 -0.0278 0.0626 1.0000
8.250 1.0086 0.02501 0.01611 -0.0271 0.0602 1.0000
8.500 1.0340 0.02658 0.01768 -0.0270 0.0578 1.0000
8.750 1.0559 0.02758 0.01887 -0.0260 0.0560 1.0000
9.000 1.0785 0.02882 0.02026 -0.0252 0.0543 1.0000
9.250 1.1003 0.03007 0.02163 -0.0244 0.0529 1.0000
9.500 1.1219 0.03133 0.02291 -0.0237 0.0515 1.0000
9.750 1.1445 0.03368 0.02533 -0.0235 0.0500 1.0000
10.000 1.1584 0.03512 0.02712 -0.0213 0.0490 1.0000
10.250 1.1718 0.03716 0.02949 -0.0192 0.0482 1.0000
10.500 1.1827 0.03948 0.03215 -0.0170 0.0476 1.0000
10.750 1.1902 0.04205 0.03505 -0.0144 0.0471 1.0000
11.000 1.1940 0.04469 0.03801 -0.0115 0.0466 1.0000
11.250 1.1948 0.04729 0.04089 -0.0084 0.0460 1.0000
11.500 1.1934 0.04975 0.04360 -0.0052 0.0455 1.0000
11.750 1.1894 0.05203 0.04606 -0.0017 0.0451 1.0000
12.000 1.1846 0.05437 0.04857 0.0015 0.0447 1.0000
12.250 1.1454 0.05940 0.05407 0.0070 0.0453 1.0000
12.500 1.0995 0.06566 0.06077 0.0106 0.0461 1.0000
12.750 1.0581 0.07238 0.06779 0.0113 0.0469 1.0000
13.000 1.0172 0.08011 0.07576 0.0094 0.0477 1.0000
13.250 0.9784 0.08922 0.08505 0.0048 0.0485 1.0000
13.500 0.9487 0.09865 0.09458 -0.0007 0.0493 1.0000
13.750 0.9332 0.10622 0.10217 -0.0044 0.0499 1.0000
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Polar data table (+)
Polar graphs
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