KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Reynolds number: 500,000 Max Cl/Cd: 88.67 at α=0.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135winglet-il-500000-n5.txt Download as CSV file: xf-kc135winglet-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4253 0.08898 0.08665 -0.0326 1.0000 0.0093
-8.500 -0.4293 0.08559 0.08331 -0.0332 1.0000 0.0093
-8.250 -0.4384 0.08295 0.08072 -0.0322 1.0000 0.0094
-8.000 -0.4283 0.07776 0.07555 -0.0382 0.9966 0.0094
-7.750 -0.4050 0.07049 0.06828 -0.0505 0.9919 0.0094
-7.500 -0.3859 0.06321 0.06094 -0.0621 0.9876 0.0097
-7.250 -0.3650 0.05866 0.05632 -0.0685 0.9839 0.0099
-7.000 -0.3408 0.05366 0.05122 -0.0755 0.9796 0.0102
-6.750 -0.3118 0.04836 0.04576 -0.0826 0.9768 0.0104
-6.500 -0.2813 0.04348 0.04068 -0.0885 0.9742 0.0107
-6.250 -0.2524 0.03917 0.03616 -0.0926 0.9695 0.0111
-6.000 -0.2192 0.03494 0.03166 -0.0967 0.9664 0.0117
-5.750 -0.1785 0.03115 0.02735 -0.0996 0.9641 0.0127
-5.500 -0.1462 0.02681 0.02280 -0.1040 0.9622 0.0133
-5.250 -0.1154 0.02484 0.02068 -0.1061 0.9585 0.0139
-5.000 -0.0803 0.02424 0.01970 -0.1069 0.9543 0.0167
-4.500 -0.0069 0.01641 0.01116 -0.1115 0.9488 0.0091
-4.250 0.0266 0.01456 0.00907 -0.1128 0.9453 0.0086
-4.000 0.0584 0.01308 0.00739 -0.1136 0.9404 0.0084
-3.750 0.0903 0.01198 0.00614 -0.1143 0.9361 0.0085
-3.500 0.1220 0.01117 0.00522 -0.1151 0.9320 0.0088
-3.250 0.1523 0.01066 0.00462 -0.1157 0.9261 0.0092
-3.000 0.1843 0.00994 0.00387 -0.1168 0.9210 0.0101
-2.750 0.2158 0.00949 0.00338 -0.1176 0.9158 0.0100
-2.500 0.2470 0.00914 0.00299 -0.1184 0.9099 0.0099
-2.250 0.2780 0.00887 0.00267 -0.1191 0.9045 0.0098
-2.000 0.3085 0.00864 0.00241 -0.1197 0.8978 0.0097
-1.750 0.3387 0.00846 0.00219 -0.1202 0.8913 0.0097
-1.500 0.3686 0.00833 0.00202 -0.1206 0.8845 0.0097
-1.250 0.3982 0.00823 0.00189 -0.1210 0.8781 0.0098
-1.000 0.4276 0.00816 0.00178 -0.1212 0.8705 0.0101
-0.750 0.4562 0.00812 0.00169 -0.1213 0.8585 0.0107
-0.500 0.4842 0.00810 0.00161 -0.1211 0.8398 0.0124
-0.250 0.5257 0.00666 0.00169 -0.1255 0.8088 0.6274
0.000 0.5526 0.00675 0.00176 -0.1250 0.7788 0.6775
0.250 0.5791 0.00688 0.00196 -0.1244 0.7509 0.7331
0.500 0.6069 0.00700 0.00198 -0.1243 0.7297 0.7389
0.750 0.6340 0.00715 0.00202 -0.1241 0.6964 0.7423
1.000 0.6582 0.00762 0.00210 -0.1232 0.6068 0.7458
1.250 0.6800 0.00856 0.00239 -0.1223 0.4652 0.7499
1.500 0.7038 0.00937 0.00268 -0.1218 0.3537 0.7542
1.750 0.7286 0.00996 0.00294 -0.1215 0.2767 0.7578
2.000 0.7545 0.01042 0.00317 -0.1213 0.2237 0.7618
2.250 0.7807 0.01083 0.00339 -0.1211 0.1810 0.7662
2.500 0.8069 0.01119 0.00363 -0.1210 0.1504 0.7702
3.000 0.8594 0.01189 0.00411 -0.1206 0.1011 0.7793
3.250 0.8859 0.01218 0.00435 -0.1204 0.0882 0.7841
3.500 0.9123 0.01245 0.00462 -0.1202 0.0801 0.7886
3.750 0.9390 0.01269 0.00488 -0.1201 0.0741 0.7936
4.000 0.9653 0.01299 0.00516 -0.1198 0.0678 0.7985
4.250 0.9917 0.01322 0.00545 -0.1196 0.0640 0.8035
4.500 1.0178 0.01351 0.00574 -0.1194 0.0586 0.8090
4.750 1.0437 0.01381 0.00606 -0.1191 0.0540 0.8142
5.000 1.0696 0.01409 0.00638 -0.1188 0.0501 0.8199
5.500 1.1206 0.01473 0.00708 -0.1181 0.0422 0.8314
5.750 1.1459 0.01505 0.00746 -0.1177 0.0379 0.8378
6.000 1.1705 0.01544 0.00787 -0.1172 0.0332 0.8439
6.250 1.1951 0.01582 0.00829 -0.1167 0.0278 0.8510
6.500 1.2188 0.01627 0.00877 -0.1160 0.0243 0.8585
6.750 1.2425 0.01673 0.00930 -0.1153 0.0226 0.8672
7.000 1.2655 0.01720 0.00984 -0.1145 0.0214 0.8773
7.250 1.2881 0.01771 0.01044 -0.1136 0.0203 0.8894
7.500 1.3096 0.01827 0.01110 -0.1125 0.0193 0.9043
7.750 1.3286 0.01881 0.01178 -0.1108 0.0185 0.9290
8.000 1.3483 0.01923 0.01232 -0.1093 0.0180 1.0000
8.250 1.3713 0.01984 0.01302 -0.1087 0.0174 1.0000
8.500 1.3938 0.02050 0.01377 -0.1079 0.0167 1.0000
8.750 1.4159 0.02116 0.01453 -0.1071 0.0160 1.0000
9.000 1.4373 0.02187 0.01535 -0.1063 0.0153 1.0000
9.250 1.4580 0.02264 0.01621 -0.1053 0.0146 1.0000
9.500 1.4775 0.02354 0.01720 -0.1041 0.0137 1.0000
9.750 1.4943 0.02472 0.01851 -0.1026 0.0129 1.0000
10.000 1.5130 0.02559 0.01951 -0.1013 0.0125 1.0000
10.250 1.5329 0.02625 0.02029 -0.1002 0.0121 1.0000
10.500 1.5517 0.02699 0.02116 -0.0990 0.0115 1.0000
10.750 1.5701 0.02772 0.02204 -0.0978 0.0106 1.0000
11.000 1.5880 0.02843 0.02285 -0.0965 0.0097 1.0000
11.250 1.6049 0.02919 0.02366 -0.0951 0.0087 1.0000
11.500 1.6189 0.03014 0.02474 -0.0932 0.0079 1.0000
11.750 1.6318 0.03106 0.02580 -0.0911 0.0069 1.0000
12.000 1.6420 0.03204 0.02686 -0.0887 0.0060 1.0000
12.250 1.6496 0.03324 0.02815 -0.0860 0.0054 1.0000
12.500 1.6551 0.03466 0.02970 -0.0832 0.0050 1.0000
12.750 1.6591 0.03624 0.03143 -0.0804 0.0047 1.0000
13.000 1.6614 0.03803 0.03338 -0.0776 0.0044 1.0000
13.250 1.6616 0.04006 0.03556 -0.0749 0.0042 1.0000
13.500 1.6598 0.04236 0.03804 -0.0724 0.0040 1.0000
13.750 1.6551 0.04503 0.04088 -0.0700 0.0038 1.0000
14.000 1.6485 0.04805 0.04409 -0.0680 0.0037 1.0000
14.250 1.6394 0.05150 0.04773 -0.0664 0.0036 1.0000
14.500 1.6289 0.05536 0.05180 -0.0654 0.0036 1.0000
14.750 1.6152 0.05992 0.05657 -0.0651 0.0036 1.0000
15.000 1.5984 0.06530 0.06216 -0.0657 0.0035 1.0000
15.250 1.5785 0.07177 0.06883 -0.0675 0.0035 1.0000
15.500 1.5524 0.08015 0.07744 -0.0713 0.0035 1.0000
15.750 1.5184 0.09174 0.08926 -0.0781 0.0036 1.0000
16.000 1.4663 0.10974 0.10756 -0.0892 0.0038 1.0000
16.250 1.3933 0.13234 0.13044 -0.1015 0.0043 1.0000
16.500 1.3233 0.15411 0.15239 -0.1139 0.0050 1.0000
16.750 1.2725 0.17287 0.17125 -0.1255 0.0055 1.0000
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Polar data table (+)
Polar graphs
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