KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Reynolds number: 50,000 Max Cl/Cd: 40.81 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135winglet-il-50000.txt Download as CSV file: xf-kc135winglet-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4256 0.09875 0.09196 -0.0185 1.0000 0.2494
-7.750 -0.4249 0.09622 0.08952 -0.0173 1.0000 0.2648
-7.500 -0.4273 0.09402 0.08742 -0.0156 1.0000 0.2812
-7.250 -0.4348 0.09225 0.08578 -0.0136 1.0000 0.2976
-7.000 -0.4465 0.09078 0.08447 -0.0123 1.0000 0.3139
-6.750 -0.4358 0.08774 0.08148 -0.0086 1.0000 0.3426
-6.500 -0.4303 0.08522 0.07903 -0.0052 1.0000 0.3718
-6.250 -0.4080 0.08156 0.07534 -0.0014 1.0000 0.4104
-6.000 -0.4109 0.07996 0.07386 0.0028 1.0000 0.4444
-5.750 -0.3968 0.07724 0.07118 0.0068 1.0000 0.4884
-5.500 -0.3662 0.07353 0.06744 0.0094 1.0000 0.5447
-5.250 -0.3633 0.07196 0.06597 0.0143 1.0000 0.5916
-5.000 -0.3170 0.06670 0.06064 0.0135 1.0000 0.6459
-4.250 -0.2466 0.04004 0.03179 -0.0699 1.0000 0.1654
-4.000 -0.2026 0.03618 0.02718 -0.0734 1.0000 0.1343
-3.750 -0.1642 0.03335 0.02372 -0.0754 1.0000 0.1184
-3.500 -0.1278 0.03137 0.02103 -0.0763 1.0000 0.1081
-3.250 -0.0968 0.02928 0.01868 -0.0767 1.0000 0.1038
-3.000 -0.0665 0.02771 0.01678 -0.0765 1.0000 0.1006
-2.750 -0.0397 0.02646 0.01536 -0.0756 1.0000 0.1006
-2.500 -0.0143 0.02544 0.01425 -0.0744 1.0000 0.1050
-2.250 0.0122 0.02464 0.01330 -0.0734 1.0000 0.1103
-2.000 0.0438 0.02359 0.01224 -0.0740 1.0000 0.1193
-1.750 0.0826 0.02255 0.01123 -0.0764 1.0000 0.1423
-1.500 0.0992 0.02028 0.01190 -0.0714 1.0000 0.8004
-1.250 0.0774 0.01975 0.01156 -0.0584 1.0000 0.9114
-1.000 0.0756 0.01922 0.01079 -0.0524 1.0000 1.0000
-0.750 0.1085 0.01953 0.01053 -0.0543 1.0000 1.0000
-0.500 0.1408 0.01987 0.01053 -0.0562 1.0000 1.0000
-0.250 0.1723 0.02025 0.01065 -0.0581 1.0000 1.0000
0.000 0.2032 0.02066 0.01086 -0.0598 1.0000 1.0000
0.250 0.2333 0.02112 0.01114 -0.0615 1.0000 1.0000
0.500 0.2628 0.02160 0.01150 -0.0630 1.0000 1.0000
0.750 0.2916 0.02213 0.01194 -0.0644 1.0000 1.0000
1.000 0.3198 0.02270 0.01244 -0.0658 1.0000 1.0000
1.250 0.3473 0.02331 0.01301 -0.0670 1.0000 1.0000
1.500 0.3742 0.02397 0.01366 -0.0682 1.0000 1.0000
1.750 0.4003 0.02468 0.01438 -0.0692 1.0000 1.0000
2.000 0.4257 0.02544 0.01519 -0.0703 1.0000 1.0000
2.250 0.4505 0.02627 0.01608 -0.0712 1.0000 1.0000
2.500 0.4744 0.02717 0.01706 -0.0722 1.0000 1.0000
2.750 0.4976 0.02815 0.01815 -0.0731 1.0000 1.0000
3.000 0.5199 0.02923 0.01940 -0.0740 1.0000 1.0000
3.250 0.5412 0.03043 0.02074 -0.0750 1.0000 1.0000
3.500 0.6090 0.03156 0.02219 -0.0840 0.9737 1.0000
3.750 0.7200 0.03050 0.02173 -0.0966 0.9150 1.0000
4.000 0.7965 0.02799 0.01978 -0.1003 0.8613 1.0000
4.250 0.8627 0.02372 0.01618 -0.0983 0.7889 1.0000
4.500 0.8918 0.02185 0.01245 -0.0875 0.4345 1.0000
4.750 0.9086 0.02483 0.01414 -0.0853 0.3212 1.0000
5.000 0.9414 0.02697 0.01593 -0.0857 0.2738 1.0000
5.250 0.9738 0.02887 0.01770 -0.0862 0.2430 1.0000
5.500 1.0075 0.03103 0.01970 -0.0869 0.2231 1.0000
5.750 1.0392 0.03334 0.02213 -0.0872 0.2089 1.0000
6.000 1.0661 0.03558 0.02459 -0.0870 0.1936 1.0000
6.250 1.0928 0.03812 0.02747 -0.0865 0.1820 1.0000
6.500 1.1157 0.04072 0.03042 -0.0857 0.1690 1.0000
6.750 1.1360 0.04391 0.03411 -0.0845 0.1592 1.0000
7.000 1.1561 0.04709 0.03751 -0.0836 0.1494 1.0000
7.250 1.1704 0.05111 0.04228 -0.0818 0.1453 1.0000
7.500 1.1823 0.05563 0.04738 -0.0800 0.1438 1.0000
7.750 1.1892 0.06055 0.05289 -0.0781 0.1435 1.0000
8.000 1.1916 0.06562 0.05846 -0.0762 0.1432 1.0000
8.250 1.1878 0.07107 0.06439 -0.0744 0.1441 1.0000
8.500 1.1786 0.07690 0.07060 -0.0728 0.1461 1.0000
8.750 1.1696 0.08282 0.07677 -0.0717 0.1489 1.0000
9.000 1.1292 0.09099 0.08529 -0.0720 0.1612 1.0000
9.250 1.0945 0.09995 0.09433 -0.0742 0.1780 1.0000
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Polar data table (+)
Polar graphs
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