KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Reynolds number: 100,000 Max Cl/Cd: 62.35 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135winglet-il-100000.txt Download as CSV file: xf-kc135winglet-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4274 0.09333 0.08841 -0.0305 1.0000 0.0751
-8.000 -0.4337 0.09085 0.08602 -0.0306 1.0000 0.0772
-7.750 -0.4434 0.08829 0.08358 -0.0325 1.0000 0.0791
-7.500 -0.4517 0.08444 0.07981 -0.0416 1.0000 0.0803
-7.250 -0.4574 0.08136 0.07653 -0.0500 1.0000 0.0810
-7.000 -0.4481 0.07696 0.07243 -0.0396 1.0000 0.0838
-6.750 -0.4439 0.07437 0.06988 -0.0379 1.0000 0.0872
-6.500 -0.4398 0.07067 0.06614 -0.0415 1.0000 0.0920
-6.250 -0.4314 0.06554 0.06082 -0.0492 1.0000 0.0969
-6.000 -0.4247 0.06304 0.05844 -0.0457 1.0000 0.1009
-5.750 -0.4063 0.05850 0.05362 -0.0526 1.0000 0.1116
-5.500 -0.3964 0.05593 0.05117 -0.0504 1.0000 0.1176
-5.250 -0.3778 0.05231 0.04743 -0.0533 1.0000 0.1302
-5.000 -0.3582 0.04924 0.04427 -0.0552 1.0000 0.1465
-4.750 -0.3361 0.04614 0.04104 -0.0579 1.0000 0.1717
-4.500 -0.3169 0.04367 0.03857 -0.0586 1.0000 0.2013
-3.500 -0.1319 0.02876 0.02096 -0.0756 1.0000 0.0929
-3.250 -0.0922 0.02608 0.01776 -0.0769 1.0000 0.0724
-3.000 -0.0600 0.02537 0.01654 -0.0767 1.0000 0.0663
-2.750 -0.0253 0.02328 0.01433 -0.0780 1.0000 0.0631
-2.500 0.0076 0.02192 0.01282 -0.0785 1.0000 0.0597
-2.250 0.0395 0.02089 0.01170 -0.0790 1.0000 0.0583
-2.000 0.0723 0.02002 0.01087 -0.0799 1.0000 0.0589
-1.750 0.1064 0.01939 0.01024 -0.0813 1.0000 0.0618
-1.500 0.1402 0.01899 0.00973 -0.0828 1.0000 0.0679
-1.250 0.1845 0.01686 0.01026 -0.0846 1.0000 0.7863
-1.000 0.1743 0.01711 0.01064 -0.0746 1.0000 0.8688
-0.750 0.1596 0.01670 0.01032 -0.0645 1.0000 0.9363
-0.500 0.1564 0.01645 0.01006 -0.0592 1.0000 1.0000
-0.250 0.1907 0.01686 0.01025 -0.0618 1.0000 1.0000
0.000 0.2243 0.01730 0.01054 -0.0642 1.0000 1.0000
0.250 0.2570 0.01779 0.01090 -0.0665 1.0000 1.0000
0.500 0.2890 0.01830 0.01133 -0.0686 1.0000 1.0000
0.750 0.3201 0.01886 0.01183 -0.0707 1.0000 1.0000
1.000 0.3504 0.01947 0.01240 -0.0726 1.0000 1.0000
1.250 0.3969 0.01998 0.01289 -0.0774 0.9919 1.0000
1.500 0.4512 0.02035 0.01327 -0.0833 0.9793 1.0000
1.750 0.5071 0.02051 0.01347 -0.0892 0.9643 1.0000
2.000 0.5662 0.02033 0.01337 -0.0950 0.9475 1.0000
2.250 0.6263 0.01957 0.01275 -0.1000 0.9254 1.0000
2.500 0.6839 0.01849 0.01181 -0.1039 0.9048 1.0000
2.750 0.7378 0.01736 0.01085 -0.1070 0.8879 1.0000
3.000 0.7760 0.01652 0.01021 -0.1072 0.8655 1.0000
3.250 0.8140 0.01546 0.00929 -0.1068 0.8366 1.0000
3.500 0.8463 0.01461 0.00853 -0.1053 0.7946 1.0000
3.750 0.8747 0.01403 0.00789 -0.1030 0.7137 1.0000
4.000 0.8871 0.01546 0.00758 -0.0979 0.3990 1.0000
4.250 0.8987 0.01796 0.00883 -0.0954 0.2459 1.0000
4.500 0.9202 0.01943 0.00990 -0.0946 0.2028 1.0000
4.750 0.9439 0.02078 0.01100 -0.0940 0.1809 1.0000
5.000 0.9699 0.02216 0.01225 -0.0938 0.1658 1.0000
5.250 0.9975 0.02344 0.01352 -0.0938 0.1537 1.0000
5.500 1.0249 0.02473 0.01487 -0.0938 0.1421 1.0000
5.750 1.0524 0.02619 0.01641 -0.0938 0.1317 1.0000
6.000 1.0777 0.02747 0.01772 -0.0936 0.1194 1.0000
6.250 1.1042 0.02924 0.01944 -0.0937 0.1094 1.0000
6.500 1.1299 0.03085 0.02138 -0.0931 0.1005 1.0000
6.750 1.1545 0.03314 0.02393 -0.0926 0.0923 1.0000
7.000 1.1783 0.03495 0.02585 -0.0921 0.0850 1.0000
7.250 1.2005 0.03834 0.02965 -0.0912 0.0815 1.0000
7.500 1.2192 0.04162 0.03357 -0.0894 0.0791 1.0000
7.750 1.2347 0.04549 0.03803 -0.0875 0.0778 1.0000
8.000 1.2458 0.04988 0.04301 -0.0852 0.0775 1.0000
8.250 1.2531 0.05423 0.04789 -0.0828 0.0765 1.0000
8.500 1.2568 0.05864 0.05276 -0.0803 0.0755 1.0000
8.750 1.2513 0.06442 0.05909 -0.0773 0.0768 1.0000
9.000 1.2415 0.07049 0.06556 -0.0746 0.0791 1.0000
9.250 1.2364 0.07616 0.07145 -0.0727 0.0812 1.0000
9.750 1.1073 0.07612 0.07192 -0.0523 0.0842 1.0000
10.000 0.9997 0.08793 0.08414 -0.0507 0.0987 1.0000
10.250 0.8987 0.11973 0.11602 -0.0671 0.1660 1.0000
|
Polar data table (+)
Polar graphs
<< Back to KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il)