KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.52 at α=1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135winglet-il-1000000.txt Download as CSV file: xf-kc135winglet-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4491 0.11698 0.11521 -0.0209 1.0000 0.0058
-10.500 -0.4443 0.11351 0.11175 -0.0223 1.0000 0.0059
-7.750 -0.4249 0.07525 0.07371 -0.0375 0.9967 0.0074
-7.500 -0.3919 0.06554 0.06397 -0.0565 0.9935 0.0076
-7.250 -0.3630 0.05782 0.05613 -0.0682 0.9899 0.0076
-7.000 -0.3321 0.05069 0.04884 -0.0776 0.9875 0.0077
-6.750 -0.3042 0.04212 0.04001 -0.0873 0.9857 0.0080
-6.500 -0.2731 0.03833 0.03607 -0.0925 0.9848 0.0082
-6.250 -0.2428 0.03492 0.03250 -0.0963 0.9824 0.0084
-6.000 -0.2101 0.03150 0.02888 -0.0999 0.9800 0.0087
-5.750 -0.1755 0.02822 0.02539 -0.1033 0.9780 0.0093
-5.500 -0.1390 0.02503 0.02193 -0.1062 0.9762 0.0101
-5.250 -0.1019 0.02293 0.01955 -0.1078 0.9744 0.0108
-5.000 -0.0632 0.01871 0.01486 -0.1114 0.9730 0.0112
-4.750 -0.0309 0.01694 0.01298 -0.1134 0.9698 0.0118
-4.500 0.0003 0.01573 0.01165 -0.1146 0.9654 0.0125
-4.250 0.0329 0.01458 0.01033 -0.1156 0.9616 0.0138
-2.750 0.2209 0.00822 0.00325 -0.1190 0.9293 0.0107
-2.500 0.2537 0.00759 0.00256 -0.1201 0.9225 0.0106
-2.250 0.2854 0.00719 0.00207 -0.1209 0.9165 0.0114
-2.000 0.3161 0.00696 0.00179 -0.1215 0.9097 0.0122
-1.750 0.3455 0.00683 0.00163 -0.1218 0.9024 0.0138
-1.500 0.3747 0.00674 0.00149 -0.1220 0.8921 0.0144
-1.250 0.4033 0.00668 0.00138 -0.1220 0.8801 0.0157
-1.000 0.4428 0.00551 0.00127 -0.1256 0.8656 0.4388
-0.750 0.4748 0.00510 0.00137 -0.1268 0.8467 0.6562
-0.500 0.5028 0.00515 0.00140 -0.1266 0.8298 0.6855
-0.250 0.5308 0.00522 0.00150 -0.1265 0.8164 0.7200
0.000 0.5591 0.00527 0.00153 -0.1265 0.8043 0.7289
0.500 0.6147 0.00548 0.00159 -0.1263 0.7621 0.7407
0.750 0.6424 0.00559 0.00163 -0.1261 0.7375 0.7462
1.000 0.6700 0.00575 0.00168 -0.1260 0.7073 0.7518
1.250 0.6965 0.00600 0.00176 -0.1257 0.6544 0.7562
1.500 0.7207 0.00667 0.00195 -0.1251 0.5431 0.7603
1.750 0.7448 0.00746 0.00222 -0.1247 0.4226 0.7646
2.000 0.7696 0.00815 0.00249 -0.1244 0.3227 0.7687
2.250 0.7951 0.00867 0.00272 -0.1241 0.2540 0.7727
2.500 0.8210 0.00915 0.00296 -0.1239 0.1972 0.7772
2.750 0.8470 0.00961 0.00320 -0.1238 0.1499 0.7817
3.000 0.8732 0.00998 0.00343 -0.1236 0.1163 0.7861
3.250 0.8998 0.01029 0.00364 -0.1234 0.0974 0.7910
3.500 0.9267 0.01055 0.00387 -0.1234 0.0867 0.7962
3.750 0.9536 0.01076 0.00409 -0.1232 0.0789 0.8011
4.000 0.9801 0.01105 0.00434 -0.1230 0.0699 0.8066
4.250 1.0072 0.01124 0.00456 -0.1229 0.0660 0.8119
4.500 1.0335 0.01151 0.00482 -0.1227 0.0603 0.8172
4.750 1.0602 0.01175 0.00508 -0.1226 0.0566 0.8231
5.000 1.0867 0.01195 0.00532 -0.1224 0.0537 0.8285
5.250 1.1128 0.01223 0.00560 -0.1221 0.0497 0.8347
5.500 1.1389 0.01251 0.00591 -0.1219 0.0458 0.8408
5.750 1.1651 0.01271 0.00616 -0.1216 0.0425 0.8473
6.000 1.1905 0.01306 0.00650 -0.1213 0.0353 0.8541
6.250 1.2151 0.01347 0.00689 -0.1208 0.0272 0.8614
6.500 1.2400 0.01385 0.00730 -0.1203 0.0249 0.8695
6.750 1.2643 0.01428 0.00777 -0.1197 0.0231 0.8789
7.000 1.2879 0.01478 0.00835 -0.1189 0.0216 0.8896
7.250 1.3104 0.01539 0.00908 -0.1179 0.0203 0.9021
7.500 1.3336 0.01569 0.00947 -0.1171 0.0198 0.9191
7.750 1.3516 0.01593 0.00984 -0.1151 0.0193 1.0000
8.000 1.3759 0.01646 0.01044 -0.1146 0.0187 1.0000
8.250 1.3998 0.01698 0.01102 -0.1141 0.0180 1.0000
8.500 1.4233 0.01752 0.01161 -0.1135 0.0172 1.0000
8.750 1.4458 0.01819 0.01233 -0.1127 0.0164 1.0000
9.000 1.4664 0.01909 0.01332 -0.1116 0.0155 1.0000
9.250 1.4840 0.02036 0.01474 -0.1100 0.0146 1.0000
9.500 1.5079 0.02068 0.01512 -0.1096 0.0143 1.0000
9.750 1.5310 0.02108 0.01558 -0.1089 0.0138 1.0000
10.000 1.5536 0.02152 0.01609 -0.1083 0.0130 1.0000
10.250 1.5763 0.02190 0.01650 -0.1077 0.0121 1.0000
10.500 1.5964 0.02258 0.01720 -0.1067 0.0110 1.0000
10.750 1.6160 0.02328 0.01799 -0.1056 0.0100 1.0000
11.000 1.6398 0.02344 0.01816 -0.1051 0.0088 1.0000
11.250 1.6601 0.02400 0.01870 -0.1042 0.0074 1.0000
11.500 1.6774 0.02485 0.01964 -0.1026 0.0065 1.0000
11.750 1.6942 0.02570 0.02055 -0.1011 0.0058 1.0000
12.000 1.7082 0.02678 0.02171 -0.0992 0.0052 1.0000
12.250 1.7161 0.02829 0.02337 -0.0963 0.0048 1.0000
12.500 1.7253 0.02944 0.02465 -0.0935 0.0046 1.0000
12.750 1.7305 0.03067 0.02602 -0.0902 0.0045 1.0000
13.000 1.7339 0.03203 0.02753 -0.0867 0.0043 1.0000
13.250 1.7364 0.03354 0.02918 -0.0835 0.0042 1.0000
13.500 1.7374 0.03524 0.03102 -0.0803 0.0041 1.0000
13.750 1.7373 0.03712 0.03305 -0.0773 0.0040 1.0000
14.000 1.7357 0.03920 0.03529 -0.0745 0.0039 1.0000
14.250 1.7324 0.04158 0.03781 -0.0719 0.0038 1.0000
14.500 1.7265 0.04431 0.04071 -0.0696 0.0038 1.0000
14.750 1.7185 0.04747 0.04403 -0.0677 0.0037 1.0000
15.000 1.7082 0.05106 0.04778 -0.0662 0.0036 1.0000
15.250 1.6948 0.05534 0.05223 -0.0654 0.0036 1.0000
15.500 1.6780 0.06040 0.05747 -0.0654 0.0036 1.0000
15.750 1.6593 0.06622 0.06348 -0.0664 0.0036 1.0000
16.000 1.6363 0.07345 0.07089 -0.0689 0.0036 1.0000
16.250 1.6076 0.08280 0.08044 -0.0735 0.0036 1.0000
16.500 1.5694 0.09579 0.09367 -0.0813 0.0037 1.0000
16.750 1.5034 0.11672 0.11491 -0.0934 0.0039 1.0000
17.000 1.4165 0.14149 0.13990 -0.1068 0.0042 1.0000
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Polar data table (+)
Polar graphs
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