KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Reynolds number: 100,000 Max Cl/Cd: 59.24 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135winglet-il-100000-n5.txt Download as CSV file: xf-kc135winglet-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4261 0.09134 0.08638 -0.0320 1.0000 0.0458
-8.000 -0.4299 0.08869 0.08381 -0.0317 1.0000 0.0466
-7.750 -0.4349 0.08599 0.08121 -0.0316 1.0000 0.0474
-7.500 -0.4372 0.08286 0.07816 -0.0329 1.0000 0.0483
-7.250 -0.4389 0.07937 0.07474 -0.0353 1.0000 0.0493
-7.000 -0.4386 0.07531 0.07071 -0.0394 1.0000 0.0504
-6.750 -0.4323 0.07091 0.06607 -0.0486 1.0000 0.0536
-6.500 -0.4214 0.06793 0.06272 -0.0534 1.0000 0.0542
-6.250 -0.4156 0.06197 0.05692 -0.0532 1.0000 0.0554
-6.000 -0.4065 0.05847 0.05350 -0.0526 1.0000 0.0567
-5.750 -0.3935 0.05531 0.05031 -0.0532 1.0000 0.0585
-5.500 -0.3754 0.05194 0.04681 -0.0552 1.0000 0.0611
-5.000 -0.2853 0.04009 0.03372 -0.0670 0.9958 0.0291
-4.750 -0.2474 0.03602 0.02929 -0.0712 0.9938 0.0263
-4.500 -0.2073 0.03267 0.02545 -0.0749 0.9917 0.0255
-4.250 -0.1683 0.03014 0.02249 -0.0780 0.9897 0.0263
-4.000 -0.1293 0.02776 0.01966 -0.0807 0.9881 0.0259
-3.750 -0.0901 0.02559 0.01700 -0.0830 0.9867 0.0246
-3.500 -0.0533 0.02387 0.01489 -0.0846 0.9847 0.0238
-3.250 -0.0185 0.02251 0.01329 -0.0859 0.9821 0.0235
-3.000 0.0164 0.02132 0.01198 -0.0873 0.9798 0.0234
-2.750 0.0517 0.02027 0.01086 -0.0889 0.9777 0.0235
-2.500 0.0884 0.01937 0.00995 -0.0909 0.9760 0.0239
-2.250 0.1245 0.01868 0.00922 -0.0929 0.9734 0.0246
-2.000 0.1593 0.01820 0.00864 -0.0946 0.9698 0.0257
-1.750 0.1956 0.01783 0.00813 -0.0966 0.9666 0.0277
-1.500 0.2330 0.01753 0.00771 -0.0987 0.9638 0.0327
-1.250 0.2752 0.01554 0.00818 -0.1026 0.9647 0.6989
-1.000 0.2934 0.01585 0.00867 -0.0990 0.9593 0.7972
-0.750 0.3152 0.01593 0.00872 -0.0970 0.9525 0.8287
-0.500 0.3389 0.01587 0.00865 -0.0952 0.9477 0.8609
-0.250 0.3657 0.01589 0.00861 -0.0950 0.9407 0.8718
0.000 0.3991 0.01589 0.00855 -0.0963 0.9362 0.8792
0.250 0.4353 0.01587 0.00848 -0.0982 0.9330 0.8859
0.500 0.4620 0.01594 0.00856 -0.0982 0.9255 0.8937
0.750 0.4974 0.01585 0.00848 -0.0997 0.9205 0.9007
1.000 0.5283 0.01576 0.00842 -0.1003 0.9114 0.9088
1.250 0.5635 0.01540 0.00809 -0.1011 0.9004 0.9161
1.500 0.5971 0.01492 0.00766 -0.1014 0.8845 0.9248
1.750 0.6286 0.01437 0.00718 -0.1009 0.8649 0.9353
2.000 0.6577 0.01390 0.00673 -0.1000 0.8409 0.9494
2.500 0.7195 0.01335 0.00623 -0.0998 0.7857 1.0000
2.750 0.7506 0.01332 0.00625 -0.1000 0.7508 1.0000
3.000 0.7812 0.01334 0.00619 -0.1000 0.6973 1.0000
3.250 0.8092 0.01366 0.00594 -0.0990 0.5667 1.0000
3.500 0.8278 0.01504 0.00630 -0.0973 0.3943 1.0000
3.750 0.8483 0.01639 0.00700 -0.0965 0.2777 1.0000
4.000 0.8718 0.01744 0.00766 -0.0963 0.2083 1.0000
4.250 0.8966 0.01833 0.00833 -0.0962 0.1700 1.0000
4.500 0.9213 0.01918 0.00905 -0.0960 0.1471 1.0000
4.750 0.9461 0.01998 0.00985 -0.0958 0.1306 1.0000
5.000 0.9706 0.02081 0.01065 -0.0955 0.1185 1.0000
5.250 0.9947 0.02167 0.01152 -0.0951 0.1100 1.0000
5.500 1.0187 0.02258 0.01252 -0.0946 0.1032 1.0000
5.750 1.0424 0.02354 0.01352 -0.0941 0.0970 1.0000
6.000 1.0665 0.02443 0.01449 -0.0937 0.0884 1.0000
6.250 1.0897 0.02524 0.01532 -0.0934 0.0790 1.0000
6.500 1.1137 0.02600 0.01622 -0.0930 0.0709 1.0000
6.750 1.1363 0.02713 0.01743 -0.0924 0.0656 1.0000
7.000 1.1594 0.02824 0.01874 -0.0917 0.0600 1.0000
7.250 1.1806 0.02958 0.02010 -0.0910 0.0557 1.0000
7.500 1.2039 0.03117 0.02199 -0.0903 0.0515 1.0000
7.750 1.2261 0.03280 0.02381 -0.0895 0.0482 1.0000
8.000 1.2466 0.03428 0.02538 -0.0887 0.0455 1.0000
8.250 1.2667 0.03628 0.02760 -0.0878 0.0430 1.0000
8.500 1.2862 0.03842 0.03020 -0.0867 0.0406 1.0000
8.750 1.3035 0.04093 0.03310 -0.0854 0.0390 1.0000
9.000 1.3181 0.04353 0.03609 -0.0838 0.0377 1.0000
9.250 1.3300 0.04621 0.03913 -0.0820 0.0366 1.0000
9.500 1.3390 0.04897 0.04223 -0.0799 0.0358 1.0000
9.750 1.3451 0.05186 0.04542 -0.0777 0.0350 1.0000
10.000 1.3477 0.05498 0.04882 -0.0753 0.0344 1.0000
10.250 1.3432 0.05873 0.05285 -0.0725 0.0337 1.0000
10.500 1.3277 0.06250 0.05709 -0.0684 0.0332 1.0000
10.750 1.3068 0.06640 0.06135 -0.0645 0.0329 1.0000
11.000 1.2836 0.07092 0.06620 -0.0618 0.0328 1.0000
11.250 1.2589 0.07612 0.07168 -0.0606 0.0327 1.0000
11.500 1.2327 0.08219 0.07799 -0.0612 0.0328 1.0000
11.750 1.2061 0.08924 0.08523 -0.0637 0.0330 1.0000
12.000 1.1797 0.09751 0.09365 -0.0682 0.0333 1.0000
12.250 1.1538 0.10737 0.10362 -0.0747 0.0337 1.0000
|
Polar data table (+)
Polar graphs
<< Back to KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il)