KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Reynolds number: 500,000 Max Cl/Cd: 103.37 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135winglet-il-500000.txt Download as CSV file: xf-kc135winglet-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3230 0.09142 0.08922 -0.0324 1.0000 0.0103
-9.250 -0.3237 0.08830 0.08612 -0.0323 1.0000 0.0106
-9.000 -0.4170 0.09475 0.09240 -0.0327 1.0000 0.0095
-8.750 -0.4150 0.09199 0.08967 -0.0319 1.0000 0.0097
-8.500 -0.4135 0.08945 0.08715 -0.0315 1.0000 0.0100
-8.250 -0.4157 0.08680 0.08455 -0.0312 1.0000 0.0101
-8.000 -0.4229 0.08456 0.08235 -0.0299 1.0000 0.0102
-7.750 -0.4382 0.08295 0.08081 -0.0267 1.0000 0.0102
-7.500 -0.4525 0.08116 0.07908 -0.0243 1.0000 0.0103
-7.250 -0.4424 0.07671 0.07465 -0.0296 0.9983 0.0104
-7.000 -0.4133 0.06960 0.06751 -0.0431 0.9952 0.0106
-6.750 -0.3837 0.06262 0.06043 -0.0551 0.9915 0.0108
-6.500 -0.3519 0.05631 0.05400 -0.0650 0.9884 0.0112
-6.250 -0.3168 0.05037 0.04789 -0.0736 0.9864 0.0116
-6.000 -0.2799 0.04491 0.04220 -0.0807 0.9844 0.0122
-5.750 -0.2381 0.04038 0.03727 -0.0855 0.9809 0.0130
-5.500 -0.2023 0.03472 0.03129 -0.0911 0.9788 0.0134
-5.250 -0.1700 0.03162 0.02811 -0.0952 0.9773 0.0141
-5.000 -0.1330 0.02891 0.02520 -0.0990 0.9762 0.0152
-4.750 -0.0893 0.02786 0.02369 -0.1012 0.9752 0.0177
-4.500 -0.0510 0.02308 0.01869 -0.1059 0.9747 0.0190
-4.250 -0.0132 0.02127 0.01675 -0.1090 0.9741 0.0211
-4.000 0.0229 0.02214 0.01727 -0.1095 0.9707 0.0244
-2.750 0.2100 0.01203 0.00624 -0.1191 0.9622 0.0181
-2.500 0.2477 0.01049 0.00467 -0.1209 0.9607 0.0133
-2.250 0.2820 0.00967 0.00384 -0.1223 0.9563 0.0126
-2.000 0.3172 0.00909 0.00320 -0.1239 0.9519 0.0126
-1.750 0.3521 0.00866 0.00271 -0.1253 0.9481 0.0145
-1.500 0.3831 0.00847 0.00251 -0.1259 0.9427 0.0216
-1.250 0.4289 0.00667 0.00253 -0.1315 0.9399 0.6574
-1.000 0.4572 0.00665 0.00258 -0.1311 0.9330 0.7034
-0.750 0.4828 0.00668 0.00262 -0.1301 0.9218 0.7314
-0.500 0.5057 0.00680 0.00279 -0.1281 0.9077 0.7686
-0.250 0.5302 0.00678 0.00271 -0.1268 0.8899 0.7756
0.000 0.5570 0.00680 0.00265 -0.1262 0.8724 0.7814
0.250 0.5838 0.00682 0.00263 -0.1257 0.8598 0.7859
0.500 0.6111 0.00686 0.00265 -0.1254 0.8465 0.7913
0.750 0.6388 0.00691 0.00265 -0.1252 0.8288 0.7966
1.000 0.6654 0.00694 0.00265 -0.1247 0.8077 0.8003
1.250 0.6925 0.00702 0.00266 -0.1243 0.7882 0.8046
1.500 0.7200 0.00713 0.00270 -0.1241 0.7642 0.8091
1.750 0.7467 0.00725 0.00274 -0.1238 0.7333 0.8132
2.000 0.7722 0.00747 0.00282 -0.1231 0.6826 0.8177
2.250 0.7942 0.00818 0.00297 -0.1219 0.5626 0.8228
2.500 0.8145 0.00925 0.00336 -0.1207 0.4158 0.8273
2.750 0.8364 0.01018 0.00375 -0.1199 0.2995 0.8320
3.000 0.8605 0.01090 0.00409 -0.1195 0.2202 0.8376
3.250 0.8845 0.01150 0.00445 -0.1190 0.1619 0.8425
3.500 0.9092 0.01201 0.00479 -0.1186 0.1273 0.8483
3.750 0.9348 0.01240 0.00511 -0.1183 0.1070 0.8545
4.000 0.9599 0.01276 0.00543 -0.1179 0.0938 0.8606
4.250 0.9854 0.01315 0.00580 -0.1175 0.0838 0.8675
4.500 1.0104 0.01342 0.00612 -0.1170 0.0777 0.8741
4.750 1.0350 0.01391 0.00660 -0.1165 0.0715 0.8819
5.000 1.0601 0.01411 0.00691 -0.1160 0.0684 0.8900
5.250 1.0849 0.01438 0.00723 -0.1155 0.0643 0.8991
5.500 1.1078 0.01490 0.00777 -0.1146 0.0593 0.9098
5.750 1.1318 0.01498 0.00796 -0.1138 0.0565 0.9231
6.000 1.1516 0.01508 0.00813 -0.1122 0.0514 0.9485
6.250 1.1756 0.01540 0.00849 -0.1116 0.0446 1.0000
6.500 1.2012 0.01603 0.00909 -0.1114 0.0356 1.0000
6.750 1.2269 0.01656 0.00963 -0.1112 0.0307 1.0000
7.000 1.2496 0.01750 0.01061 -0.1104 0.0276 1.0000
7.250 1.2741 0.01807 0.01126 -0.1100 0.0260 1.0000
7.500 1.2987 0.01857 0.01179 -0.1096 0.0240 1.0000
7.750 1.3211 0.01936 0.01259 -0.1089 0.0220 1.0000
8.000 1.3411 0.02049 0.01383 -0.1077 0.0206 1.0000
8.250 1.3651 0.02093 0.01436 -0.1073 0.0194 1.0000
8.500 1.3883 0.02144 0.01494 -0.1067 0.0180 1.0000
8.750 1.4099 0.02216 0.01573 -0.1059 0.0170 1.0000
9.000 1.4295 0.02311 0.01674 -0.1048 0.0157 1.0000
9.250 1.4468 0.02434 0.01810 -0.1034 0.0146 1.0000
9.500 1.4715 0.02446 0.01830 -0.1031 0.0137 1.0000
9.750 1.4942 0.02483 0.01874 -0.1025 0.0127 1.0000
10.000 1.5170 0.02515 0.01911 -0.1020 0.0116 1.0000
10.250 1.5363 0.02589 0.01990 -0.1010 0.0105 1.0000
10.500 1.5571 0.02640 0.02050 -0.1001 0.0095 1.0000
10.750 1.5782 0.02684 0.02103 -0.0992 0.0081 1.0000
11.000 1.5968 0.02754 0.02179 -0.0980 0.0068 1.0000
11.250 1.6131 0.02843 0.02280 -0.0964 0.0051 1.0000
11.750 1.6333 0.03121 0.02575 -0.0916 0.0024 1.0000
12.000 1.6386 0.03268 0.02740 -0.0884 0.0022 1.0000
12.250 1.6414 0.03434 0.02923 -0.0850 0.0020 1.0000
12.500 1.6428 0.03616 0.03125 -0.0817 0.0019 1.0000
12.750 1.6420 0.03824 0.03353 -0.0785 0.0018 1.0000
13.000 1.6398 0.04050 0.03600 -0.0755 0.0017 1.0000
13.250 1.6352 0.04309 0.03881 -0.0726 0.0016 1.0000
13.500 1.6282 0.04603 0.04197 -0.0701 0.0015 1.0000
13.750 1.6193 0.04934 0.04549 -0.0680 0.0015 1.0000
14.000 1.6085 0.05303 0.04941 -0.0665 0.0015 1.0000
14.250 1.5949 0.05737 0.05397 -0.0656 0.0014 1.0000
14.500 1.5782 0.06247 0.05929 -0.0656 0.0014 1.0000
14.750 1.5586 0.06852 0.06555 -0.0668 0.0014 1.0000
15.000 1.5346 0.07607 0.07333 -0.0697 0.0014 1.0000
15.250 1.5053 0.08595 0.08342 -0.0751 0.0015 1.0000
15.500 1.4678 0.09979 0.09751 -0.0839 0.0015 1.0000
15.750 1.4193 0.11760 0.11557 -0.0941 0.0018 1.0000
16.000 1.3638 0.13572 0.13386 -0.1036 0.0021 1.0000
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Polar data table (+)
Polar graphs
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