KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Reynolds number: 200,000 Max Cl/Cd: 85.6 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135winglet-il-200000.txt Download as CSV file: xf-kc135winglet-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: KC-135 Winglet (supercritical Whitcomb)
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4314 0.09966 0.09605 -0.0367 1.0000 0.0287
-8.750 -0.4344 0.09664 0.09309 -0.0377 1.0000 0.0288
-8.500 -0.4380 0.09090 0.08742 -0.0361 1.0000 0.0295
-8.250 -0.4305 0.08803 0.08456 -0.0331 1.0000 0.0307
-8.000 -0.4336 0.08567 0.08225 -0.0318 1.0000 0.0314
-7.750 -0.4398 0.08333 0.07998 -0.0306 1.0000 0.0321
-7.500 -0.4440 0.08061 0.07732 -0.0307 1.0000 0.0328
-7.250 -0.4483 0.07758 0.07433 -0.0318 1.0000 0.0336
-7.000 -0.4508 0.07392 0.07072 -0.0346 1.0000 0.0342
-6.750 -0.4500 0.07002 0.06680 -0.0377 1.0000 0.0350
-6.500 -0.4450 0.06599 0.06272 -0.0409 1.0000 0.0361
-6.250 -0.4331 0.06171 0.05831 -0.0451 1.0000 0.0377
-6.000 -0.4067 0.05904 0.05512 -0.0512 1.0000 0.0396
-5.750 -0.3916 0.05230 0.04819 -0.0550 1.0000 0.0406
-5.500 -0.3790 0.04824 0.04424 -0.0555 1.0000 0.0419
-5.250 -0.3611 0.04536 0.04132 -0.0566 1.0000 0.0437
-5.000 -0.3363 0.04239 0.03819 -0.0589 0.9999 0.0466
-3.000 -0.0008 0.02102 0.01378 -0.0868 0.9880 0.0409
-2.750 0.0383 0.01901 0.01166 -0.0887 0.9876 0.0341
-2.500 0.0782 0.01774 0.01020 -0.0905 0.9866 0.0308
-2.250 0.1181 0.01689 0.00940 -0.0932 0.9855 0.0345
-2.000 0.1602 0.01609 0.00861 -0.0962 0.9845 0.0359
-1.750 0.1998 0.01548 0.00796 -0.0989 0.9813 0.0374
-1.500 0.2412 0.01503 0.00739 -0.1019 0.9782 0.0418
-1.250 0.2912 0.01322 0.00792 -0.1069 0.9809 0.7536
-1.000 0.3119 0.01362 0.00845 -0.1039 0.9751 0.8147
-0.750 0.3370 0.01377 0.00863 -0.1023 0.9712 0.8474
-0.500 0.3542 0.01382 0.00872 -0.0994 0.9640 0.8725
-0.250 0.3917 0.01381 0.00865 -0.1016 0.9606 0.8809
0.000 0.4235 0.01374 0.00857 -0.1025 0.9550 0.8876
0.250 0.4624 0.01355 0.00836 -0.1047 0.9481 0.8945
0.500 0.5037 0.01309 0.00790 -0.1069 0.9404 0.9000
0.750 0.5520 0.01234 0.00717 -0.1101 0.9314 0.9049
1.000 0.5898 0.01162 0.00646 -0.1110 0.9178 0.9102
1.250 0.6204 0.01109 0.00595 -0.1105 0.9040 0.9164
1.500 0.6483 0.01079 0.00569 -0.1099 0.8913 0.9235
1.750 0.6742 0.01053 0.00549 -0.1089 0.8787 0.9315
2.000 0.6996 0.01024 0.00523 -0.1077 0.8635 0.9400
2.250 0.7246 0.00992 0.00493 -0.1063 0.8446 0.9504
2.500 0.7471 0.00967 0.00471 -0.1045 0.8206 0.9663
2.750 0.7759 0.00946 0.00451 -0.1041 0.7908 1.0000
3.000 0.8066 0.00950 0.00447 -0.1044 0.7472 1.0000
3.250 0.8346 0.00975 0.00441 -0.1039 0.6563 1.0000
3.500 0.8513 0.01122 0.00470 -0.1017 0.4431 1.0000
3.750 0.8690 0.01306 0.00555 -0.1008 0.2632 1.0000
4.000 0.8923 0.01440 0.00633 -0.1008 0.1785 1.0000
4.250 0.9182 0.01537 0.00709 -0.1009 0.1485 1.0000
4.500 0.9446 0.01622 0.00786 -0.1010 0.1323 1.0000
4.750 0.9706 0.01709 0.00867 -0.1010 0.1208 1.0000
5.000 0.9961 0.01797 0.00945 -0.1010 0.1100 1.0000
5.250 1.0233 0.01850 0.01008 -0.1011 0.1017 1.0000
5.500 1.0482 0.01947 0.01101 -0.1009 0.0947 1.0000
5.750 1.0743 0.02009 0.01171 -0.1008 0.0876 1.0000
6.000 1.0988 0.02110 0.01273 -0.1005 0.0807 1.0000
6.250 1.1240 0.02176 0.01347 -0.1002 0.0733 1.0000
6.500 1.1480 0.02303 0.01484 -0.0997 0.0660 1.0000
6.750 1.1719 0.02407 0.01588 -0.0992 0.0596 1.0000
7.000 1.1963 0.02592 0.01789 -0.0986 0.0551 1.0000
7.250 1.2210 0.02738 0.01954 -0.0980 0.0518 1.0000
7.500 1.2445 0.02865 0.02090 -0.0974 0.0490 1.0000
7.750 1.2669 0.03188 0.02429 -0.0970 0.0462 1.0000
8.000 1.2885 0.03367 0.02644 -0.0959 0.0453 1.0000
8.250 1.3080 0.03613 0.02932 -0.0945 0.0442 1.0000
8.500 1.3240 0.03925 0.03289 -0.0927 0.0434 1.0000
8.750 1.3364 0.04248 0.03660 -0.0905 0.0422 1.0000
9.000 1.3474 0.04527 0.03975 -0.0883 0.0406 1.0000
9.250 1.3569 0.04800 0.04277 -0.0862 0.0393 1.0000
9.500 1.3733 0.04878 0.04351 -0.0853 0.0373 1.0000
10.000 1.3560 0.05788 0.05347 -0.0780 0.0352 1.0000
10.250 1.3410 0.06188 0.05789 -0.0737 0.0346 1.0000
10.500 1.3178 0.06587 0.06218 -0.0689 0.0345 1.0000
10.750 1.2924 0.07025 0.06682 -0.0653 0.0345 1.0000
11.000 1.2657 0.07534 0.07212 -0.0633 0.0347 1.0000
11.250 1.2390 0.08114 0.07811 -0.0631 0.0350 1.0000
11.500 1.2121 0.08787 0.08496 -0.0646 0.0354 1.0000
11.750 1.1865 0.09580 0.09297 -0.0674 0.0359 1.0000
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Polar data table (+)
Polar graphs
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