KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.15 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135winglet-il-1000000-n5.txt Download as CSV file: xf-kc135winglet-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4270 0.09127 0.08960 -0.0305 1.0000 0.0051
-8.750 -0.4270 0.08823 0.08658 -0.0311 1.0000 0.0052
-8.500 -0.4280 0.08517 0.08355 -0.0316 0.9997 0.0054
-8.250 -0.4165 0.08060 0.07898 -0.0366 0.9966 0.0059
-8.000 -0.4020 0.07446 0.07284 -0.0446 0.9907 0.0065
-7.750 -0.3792 0.06729 0.06568 -0.0567 0.9867 0.0066
-7.500 -0.3540 0.05918 0.05748 -0.0711 0.9797 0.0066
-7.250 -0.3277 0.05260 0.05078 -0.0804 0.9754 0.0066
-7.000 -0.3030 0.04720 0.04523 -0.0864 0.9693 0.0067
-6.750 -0.2754 0.04223 0.04008 -0.0915 0.9643 0.0067
-6.500 -0.2475 0.03777 0.03541 -0.0956 0.9595 0.0067
-6.250 -0.2196 0.03376 0.03119 -0.0986 0.9534 0.0067
-6.000 -0.1897 0.03007 0.02726 -0.1014 0.9482 0.0067
-5.750 -0.1598 0.02674 0.02367 -0.1036 0.9423 0.0067
-5.500 -0.1288 0.02372 0.02037 -0.1055 0.9362 0.0067
-5.250 -0.0971 0.02101 0.01738 -0.1073 0.9309 0.0067
-5.000 -0.0651 0.01866 0.01475 -0.1089 0.9252 0.0067
-4.750 -0.0330 0.01662 0.01242 -0.1102 0.9198 0.0067
-4.500 0.0003 0.01376 0.00930 -0.1123 0.9150 0.0060
-4.250 0.0326 0.01197 0.00725 -0.1132 0.9095 0.0056
-4.000 0.0639 0.01073 0.00582 -0.1138 0.9042 0.0057
-3.750 0.0948 0.00991 0.00488 -0.1144 0.8981 0.0059
-3.500 0.1250 0.00941 0.00427 -0.1149 0.8917 0.0064
-3.250 0.1548 0.00914 0.00392 -0.1153 0.8853 0.0067
-3.000 0.1860 0.00856 0.00327 -0.1162 0.8786 0.0069
-2.750 0.2178 0.00804 0.00272 -0.1172 0.8723 0.0073
-2.500 0.2485 0.00775 0.00242 -0.1180 0.8655 0.0081
-2.250 0.2793 0.00751 0.00213 -0.1187 0.8595 0.0080
-2.000 0.3101 0.00730 0.00189 -0.1194 0.8535 0.0078
-1.750 0.3401 0.00717 0.00170 -0.1198 0.8459 0.0076
-1.500 0.3697 0.00707 0.00155 -0.1202 0.8324 0.0075
-1.250 0.3989 0.00701 0.00142 -0.1204 0.8140 0.0075
-1.000 0.4274 0.00703 0.00132 -0.1205 0.7900 0.0074
-0.750 0.4555 0.00710 0.00125 -0.1205 0.7598 0.0075
-0.500 0.4836 0.00718 0.00120 -0.1205 0.7230 0.0076
-0.250 0.5116 0.00731 0.00117 -0.1206 0.6861 0.0078
0.000 0.5395 0.00747 0.00118 -0.1206 0.6421 0.0084
0.250 0.5782 0.00683 0.00139 -0.1246 0.5258 0.5768
0.500 0.6038 0.00755 0.00176 -0.1246 0.3818 0.6728
0.750 0.6300 0.00804 0.00199 -0.1245 0.3003 0.7032
1.000 0.6570 0.00839 0.00213 -0.1245 0.2518 0.7093
1.250 0.6841 0.00869 0.00228 -0.1245 0.2115 0.7130
1.500 0.7112 0.00899 0.00243 -0.1244 0.1756 0.7165
1.750 0.7384 0.00926 0.00257 -0.1244 0.1490 0.7205
2.000 0.7654 0.00956 0.00274 -0.1243 0.1194 0.7243
2.250 0.7924 0.00986 0.00292 -0.1243 0.0946 0.7275
2.500 0.8198 0.01005 0.00308 -0.1243 0.0850 0.7311
2.750 0.8473 0.01023 0.00324 -0.1242 0.0776 0.7350
3.000 0.8745 0.01044 0.00341 -0.1242 0.0700 0.7388
3.250 0.9019 0.01062 0.00360 -0.1241 0.0647 0.7426
3.500 0.9289 0.01083 0.00379 -0.1241 0.0583 0.7470
3.750 0.9560 0.01105 0.00400 -0.1240 0.0531 0.7518
4.000 0.9829 0.01127 0.00420 -0.1239 0.0486 0.7564
4.250 1.0096 0.01150 0.00445 -0.1237 0.0439 0.7615
4.500 1.0365 0.01171 0.00467 -0.1236 0.0417 0.7665
4.750 1.0631 0.01195 0.00492 -0.1234 0.0378 0.7711
5.000 1.0894 0.01222 0.00519 -0.1232 0.0334 0.7761
5.250 1.1154 0.01253 0.00549 -0.1230 0.0260 0.7813
5.500 1.1408 0.01292 0.00584 -0.1226 0.0208 0.7861
5.750 1.1667 0.01322 0.00618 -0.1223 0.0184 0.7915
6.000 1.1925 0.01352 0.00652 -0.1220 0.0178 0.7969
6.250 1.2181 0.01383 0.00688 -0.1217 0.0173 0.8024
6.500 1.2435 0.01417 0.00728 -0.1213 0.0168 0.8083
6.750 1.2685 0.01454 0.00770 -0.1209 0.0161 0.8138
7.000 1.2932 0.01494 0.00815 -0.1204 0.0152 0.8198
7.250 1.3177 0.01538 0.00862 -0.1199 0.0143 0.8257
7.500 1.3418 0.01584 0.00917 -0.1193 0.0135 0.8314
7.750 1.3654 0.01636 0.00978 -0.1186 0.0129 0.8377
8.000 1.3890 0.01683 0.01033 -0.1180 0.0126 0.8443
8.250 1.4131 0.01720 0.01077 -0.1174 0.0124 0.8520
8.500 1.4366 0.01760 0.01126 -0.1168 0.0122 0.8604
8.750 1.4599 0.01801 0.01177 -0.1161 0.0119 0.8704
9.250 1.5050 0.01880 0.01275 -0.1145 0.0109 0.9001
9.500 1.5251 0.01914 0.01319 -0.1132 0.0100 0.9298
9.750 1.5442 0.01955 0.01366 -0.1117 0.0092 1.0000
10.000 1.5657 0.02017 0.01433 -0.1108 0.0084 1.0000
10.250 1.5876 0.02068 0.01492 -0.1100 0.0078 1.0000
10.500 1.6087 0.02127 0.01554 -0.1091 0.0060 1.0000
10.750 1.6276 0.02211 0.01636 -0.1079 0.0044 1.0000
11.000 1.6459 0.02298 0.01730 -0.1065 0.0036 1.0000
11.250 1.6635 0.02387 0.01828 -0.1051 0.0033 1.0000
11.500 1.6802 0.02480 0.01932 -0.1035 0.0031 1.0000
11.750 1.6956 0.02581 0.02044 -0.1017 0.0029 1.0000
12.000 1.7095 0.02688 0.02163 -0.0997 0.0027 1.0000
12.250 1.7214 0.02802 0.02291 -0.0974 0.0025 1.0000
12.500 1.7307 0.02922 0.02424 -0.0948 0.0024 1.0000
12.750 1.7366 0.03048 0.02564 -0.0916 0.0023 1.0000
13.000 1.7394 0.03191 0.02721 -0.0880 0.0022 1.0000
13.250 1.7437 0.03326 0.02869 -0.0849 0.0022 1.0000
13.500 1.7467 0.03478 0.03036 -0.0819 0.0022 1.0000
13.750 1.7487 0.03645 0.03217 -0.0790 0.0021 1.0000
14.000 1.7490 0.03833 0.03419 -0.0763 0.0021 1.0000
14.250 1.7479 0.04043 0.03644 -0.0737 0.0021 1.0000
14.500 1.7451 0.04279 0.03895 -0.0713 0.0020 1.0000
14.750 1.7400 0.04551 0.04184 -0.0692 0.0020 1.0000
15.000 1.7331 0.04857 0.04506 -0.0674 0.0020 1.0000
15.250 1.7242 0.05205 0.04871 -0.0661 0.0020 1.0000
15.500 1.7123 0.05617 0.05299 -0.0654 0.0019 1.0000
15.750 1.6973 0.06095 0.05794 -0.0653 0.0019 1.0000
16.000 1.6787 0.06671 0.06389 -0.0663 0.0019 1.0000
16.250 1.6551 0.07393 0.07130 -0.0687 0.0019 1.0000
16.500 1.6240 0.08359 0.08117 -0.0734 0.0019 1.0000
16.750 1.5749 0.09907 0.09691 -0.0829 0.0020 1.0000
17.000 1.3920 0.14796 0.14628 -0.1105 0.0023 1.0000
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Polar data table (+)
Polar graphs
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