KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Reynolds number: 200,000 Max Cl/Cd: 73.15 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135winglet-il-200000-n5.txt Download as CSV file: xf-kc135winglet-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4359 0.09085 0.08732 -0.0375 1.0000 0.0225
-8.250 -0.4421 0.08666 0.08321 -0.0361 1.0000 0.0228
-8.000 -0.4440 0.08363 0.08024 -0.0349 1.0000 0.0231
-7.750 -0.4465 0.08074 0.07740 -0.0346 1.0000 0.0234
-7.500 -0.4493 0.07767 0.07438 -0.0354 1.0000 0.0236
-7.250 -0.4495 0.07395 0.07069 -0.0381 0.9997 0.0238
-7.000 -0.4261 0.06842 0.06509 -0.0462 0.9960 0.0244
-6.750 -0.4008 0.06288 0.05944 -0.0542 0.9918 0.0251
-6.500 -0.3721 0.05735 0.05377 -0.0621 0.9880 0.0259
-6.250 -0.3410 0.05209 0.04830 -0.0692 0.9845 0.0270
-6.000 -0.3073 0.04726 0.04318 -0.0752 0.9804 0.0286
-5.750 -0.2621 0.04450 0.03976 -0.0811 0.9775 0.0306
-5.500 -0.2262 0.04101 0.03588 -0.0853 0.9757 0.0307
-5.250 -0.1967 0.03431 0.02905 -0.0899 0.9734 0.0320
-5.000 -0.1610 0.03038 0.02479 -0.0919 0.9704 0.0215
-4.750 -0.1215 0.02601 0.01991 -0.0950 0.9685 0.0160
-4.500 -0.0841 0.02339 0.01696 -0.0977 0.9666 0.0150
-4.250 -0.0456 0.02099 0.01416 -0.1000 0.9650 0.0142
-4.000 -0.0078 0.01902 0.01182 -0.1019 0.9636 0.0138
-3.750 0.0284 0.01786 0.01048 -0.1038 0.9623 0.0149
-3.500 0.0626 0.01681 0.00924 -0.1051 0.9600 0.0160
-3.250 0.0947 0.01574 0.00808 -0.1059 0.9564 0.0158
-3.000 0.1291 0.01479 0.00708 -0.1074 0.9538 0.0156
-2.750 0.1649 0.01398 0.00625 -0.1092 0.9515 0.0156
-2.500 0.2020 0.01330 0.00555 -0.1114 0.9494 0.0156
-2.250 0.2396 0.01279 0.00496 -0.1137 0.9476 0.0158
-2.000 0.2718 0.01247 0.00457 -0.1147 0.9428 0.0162
-1.750 0.3053 0.01222 0.00424 -0.1160 0.9387 0.0168
-1.500 0.3402 0.01198 0.00397 -0.1175 0.9355 0.0190
-1.250 0.3864 0.01011 0.00407 -0.1232 0.9349 0.6157
-1.000 0.4161 0.01009 0.00419 -0.1232 0.9295 0.6870
-0.750 0.4446 0.01013 0.00430 -0.1229 0.9231 0.7287
-0.500 0.4737 0.01017 0.00441 -0.1226 0.9188 0.7618
-0.250 0.4975 0.01031 0.00461 -0.1212 0.9115 0.7880
0.000 0.5287 0.01026 0.00454 -0.1217 0.9056 0.7938
0.250 0.5576 0.01017 0.00442 -0.1216 0.8927 0.7986
0.500 0.5852 0.01001 0.00422 -0.1208 0.8729 0.8028
0.750 0.6124 0.00990 0.00403 -0.1200 0.8470 0.8074
1.000 0.6392 0.00988 0.00393 -0.1193 0.8192 0.8124
1.250 0.6656 0.00989 0.00390 -0.1186 0.7953 0.8167
1.500 0.6929 0.00994 0.00391 -0.1182 0.7732 0.8216
1.750 0.7201 0.01003 0.00395 -0.1178 0.7444 0.8266
2.000 0.7447 0.01018 0.00395 -0.1167 0.6909 0.8311
2.250 0.7653 0.01078 0.00396 -0.1148 0.5678 0.8368
2.500 0.7829 0.01185 0.00433 -0.1129 0.4278 0.8423
2.750 0.8029 0.01277 0.00475 -0.1117 0.3241 0.8480
3.250 0.8479 0.01415 0.00553 -0.1102 0.1946 0.8598
3.500 0.8716 0.01473 0.00595 -0.1097 0.1554 0.8667
3.750 0.8950 0.01519 0.00633 -0.1089 0.1315 0.8734
4.000 0.9193 0.01563 0.00673 -0.1084 0.1158 0.8815
4.250 0.9425 0.01604 0.00713 -0.1075 0.1045 0.8902
4.500 0.9653 0.01649 0.00758 -0.1067 0.0945 0.9007
4.750 0.9879 0.01683 0.00799 -0.1057 0.0863 0.9135
5.000 1.0083 0.01722 0.00840 -0.1043 0.0799 0.9321
5.250 1.0300 0.01749 0.00880 -0.1031 0.0744 1.0000
5.500 1.0558 0.01810 0.00938 -0.1031 0.0682 1.0000
5.750 1.0821 0.01858 0.00996 -0.1031 0.0635 1.0000
6.000 1.1076 0.01913 0.01058 -0.1029 0.0587 1.0000
6.250 1.1322 0.01980 0.01127 -0.1026 0.0544 1.0000
6.500 1.1571 0.02037 0.01197 -0.1023 0.0497 1.0000
6.750 1.1804 0.02114 0.01273 -0.1018 0.0445 1.0000
7.000 1.2043 0.02183 0.01357 -0.1012 0.0401 1.0000
7.250 1.2274 0.02257 0.01438 -0.1007 0.0360 1.0000
7.500 1.2483 0.02364 0.01549 -0.0997 0.0334 1.0000
7.750 1.2700 0.02462 0.01664 -0.0988 0.0316 1.0000
8.000 1.2910 0.02568 0.01784 -0.0978 0.0301 1.0000
8.250 1.3116 0.02676 0.01909 -0.0968 0.0288 1.0000
8.500 1.3317 0.02788 0.02034 -0.0958 0.0277 1.0000
8.750 1.3507 0.02909 0.02168 -0.0946 0.0268 1.0000
9.000 1.3680 0.03060 0.02333 -0.0932 0.0260 1.0000
9.250 1.3846 0.03236 0.02527 -0.0918 0.0253 1.0000
9.500 1.4020 0.03375 0.02697 -0.0904 0.0243 1.0000
9.750 1.4184 0.03492 0.02837 -0.0890 0.0227 1.0000
10.000 1.4333 0.03605 0.02968 -0.0874 0.0214 1.0000
10.250 1.4463 0.03721 0.03100 -0.0856 0.0204 1.0000
10.500 1.4555 0.03869 0.03261 -0.0834 0.0194 1.0000
10.750 1.4584 0.04100 0.03513 -0.0805 0.0185 1.0000
11.000 1.4611 0.04284 0.03730 -0.0773 0.0179 1.0000
11.250 1.4619 0.04489 0.03967 -0.0743 0.0170 1.0000
11.500 1.4601 0.04719 0.04226 -0.0714 0.0162 1.0000
11.750 1.4577 0.04949 0.04479 -0.0688 0.0154 1.0000
12.000 1.4537 0.05202 0.04756 -0.0666 0.0147 1.0000
12.250 1.4479 0.05483 0.05057 -0.0647 0.0142 1.0000
12.500 1.4393 0.05818 0.05411 -0.0634 0.0138 1.0000
12.750 1.4268 0.06229 0.05844 -0.0626 0.0135 1.0000
13.000 1.4111 0.06720 0.06355 -0.0628 0.0132 1.0000
13.250 1.3918 0.07317 0.06974 -0.0641 0.0131 1.0000
13.500 1.3697 0.08040 0.07721 -0.0670 0.0130 1.0000
13.750 1.3442 0.08952 0.08661 -0.0721 0.0132 1.0000
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Polar data table (+)
Polar graphs
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