KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Reynolds number: 50,000 Max Cl/Cd: 40.89 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135winglet-il-50000-n5.txt Download as CSV file: xf-kc135winglet-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4416 0.09882 0.09199 -0.0286 1.0000 0.1296
-8.000 -0.4397 0.09618 0.08941 -0.0277 1.0000 0.1367
-7.750 -0.4641 0.09428 0.08772 -0.0355 1.0000 0.1410
-7.500 -0.4431 0.09060 0.08405 -0.0274 1.0000 0.1497
-7.000 -0.4578 0.08458 0.07826 -0.0363 1.0000 0.1704
-6.000 -0.3996 0.06256 0.05552 -0.0548 1.0000 0.0819
-5.750 -0.3826 0.05776 0.05068 -0.0549 1.0000 0.0635
-5.500 -0.3543 0.05279 0.04517 -0.0593 1.0000 0.0522
-5.250 -0.3328 0.04893 0.04113 -0.0612 1.0000 0.0493
-5.000 -0.3045 0.04494 0.03670 -0.0641 1.0000 0.0459
-4.750 -0.2669 0.04171 0.03253 -0.0672 1.0000 0.0417
-4.500 -0.2394 0.03888 0.02939 -0.0685 1.0000 0.0406
-4.250 -0.2101 0.03611 0.02629 -0.0701 1.0000 0.0399
-4.000 -0.1799 0.03374 0.02356 -0.0713 1.0000 0.0393
-3.750 -0.1500 0.03173 0.02120 -0.0721 1.0000 0.0388
-3.500 -0.1206 0.03001 0.01913 -0.0726 1.0000 0.0386
-3.250 -0.0925 0.02856 0.01742 -0.0726 1.0000 0.0386
-3.000 -0.0658 0.02736 0.01601 -0.0722 1.0000 0.0388
-2.750 -0.0408 0.02644 0.01492 -0.0713 1.0000 0.0400
-2.500 -0.0154 0.02561 0.01396 -0.0706 1.0000 0.0419
-2.250 0.0128 0.02472 0.01298 -0.0710 1.0000 0.0451
-2.000 0.0434 0.02409 0.01220 -0.0719 1.0000 0.0486
-1.750 0.0754 0.02358 0.01149 -0.0731 1.0000 0.0525
-1.500 0.1099 0.02302 0.01082 -0.0750 1.0000 0.0612
-1.250 0.1445 0.02057 0.01131 -0.0760 1.0000 0.7451
-1.000 0.1310 0.02044 0.01146 -0.0651 1.0000 0.8706
-0.750 0.1120 0.01963 0.01086 -0.0552 1.0000 0.9882
-0.500 0.1424 0.01994 0.01076 -0.0567 1.0000 1.0000
-0.250 0.1740 0.02032 0.01084 -0.0586 1.0000 1.0000
0.000 0.2105 0.02074 0.01100 -0.0613 0.9968 1.0000
0.250 0.2501 0.02117 0.01123 -0.0647 0.9913 1.0000
0.500 0.2912 0.02165 0.01156 -0.0682 0.9864 1.0000
0.750 0.3282 0.02208 0.01188 -0.0710 0.9797 1.0000
1.000 0.3689 0.02256 0.01228 -0.0745 0.9739 1.0000
1.250 0.4061 0.02299 0.01268 -0.0772 0.9656 1.0000
1.500 0.4454 0.02341 0.01311 -0.0802 0.9571 1.0000
1.750 0.4872 0.02380 0.01355 -0.0836 0.9483 1.0000
2.000 0.5246 0.02413 0.01394 -0.0859 0.9367 1.0000
2.250 0.5676 0.02425 0.01418 -0.0889 0.9219 1.0000
2.500 0.6155 0.02408 0.01419 -0.0922 0.9046 1.0000
2.750 0.6567 0.02368 0.01396 -0.0938 0.8804 1.0000
3.000 0.7020 0.02283 0.01330 -0.0951 0.8520 1.0000
3.250 0.7424 0.02182 0.01252 -0.0950 0.8178 1.0000
3.500 0.7735 0.02117 0.01203 -0.0936 0.7771 1.0000
3.750 0.8005 0.02081 0.01181 -0.0919 0.7248 1.0000
4.000 0.8305 0.02041 0.01143 -0.0902 0.6317 1.0000
4.250 0.8590 0.02101 0.01080 -0.0878 0.4285 1.0000
4.500 0.8724 0.02292 0.01179 -0.0856 0.3015 1.0000
4.750 0.8902 0.02457 0.01296 -0.0844 0.2371 1.0000
5.000 0.9114 0.02596 0.01412 -0.0837 0.1992 1.0000
5.250 0.9342 0.02728 0.01536 -0.0832 0.1763 1.0000
5.500 0.9595 0.02856 0.01666 -0.0829 0.1607 1.0000
5.750 0.9864 0.02983 0.01798 -0.0828 0.1465 1.0000
6.000 1.0134 0.03115 0.01936 -0.0828 0.1338 1.0000
6.250 1.0430 0.03262 0.02098 -0.0829 0.1247 1.0000
6.500 1.0726 0.03434 0.02290 -0.0831 0.1160 1.0000
6.750 1.0977 0.03596 0.02461 -0.0829 0.1062 1.0000
7.000 1.1215 0.03758 0.02644 -0.0825 0.0966 1.0000
7.250 1.1449 0.03960 0.02881 -0.0820 0.0881 1.0000
7.500 1.1671 0.04154 0.03080 -0.0816 0.0816 1.0000
7.750 1.1867 0.04403 0.03390 -0.0805 0.0747 1.0000
8.000 1.2058 0.04640 0.03653 -0.0796 0.0701 1.0000
8.250 1.2241 0.04940 0.03970 -0.0788 0.0674 1.0000
8.500 1.2349 0.05341 0.04448 -0.0768 0.0653 1.0000
8.750 1.2410 0.05763 0.04932 -0.0746 0.0636 1.0000
9.000 1.2424 0.06197 0.05421 -0.0723 0.0624 1.0000
9.250 1.2392 0.06635 0.05906 -0.0699 0.0614 1.0000
9.500 1.2320 0.07063 0.06373 -0.0675 0.0604 1.0000
9.750 1.2216 0.07472 0.06814 -0.0652 0.0594 1.0000
10.000 1.2053 0.07880 0.07247 -0.0627 0.0588 1.0000
10.250 1.1814 0.08357 0.07748 -0.0608 0.0588 1.0000
10.500 1.1479 0.09018 0.08433 -0.0610 0.0596 1.0000
10.750 1.1119 0.09870 0.09300 -0.0645 0.0610 1.0000
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Polar data table (+)
Polar graphs
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