KC-135 BL52.44 AIRFOIL (kc135a-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: KC-135 BL52.44 AIRFOIL (kc135a-il) Reynolds number: 100,000 Max Cl/Cd: 47.35 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135a-il-100000.txt Download as CSV file: xf-kc135a-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: KC-135 BL52.44 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5012 0.10291 0.09789 -0.0371 1.0000 0.1686
-10.750 -0.4524 0.10157 0.09649 -0.0311 1.0000 0.1743
-10.500 -0.5052 0.09502 0.09012 -0.0379 1.0000 0.1858
-10.250 -0.4491 0.09522 0.09023 -0.0315 1.0000 0.1932
-10.000 -0.4571 0.09150 0.08658 -0.0323 1.0000 0.2053
-9.750 -0.4677 0.08802 0.08318 -0.0329 1.0000 0.2196
-9.500 -0.4725 0.08517 0.08041 -0.0326 1.0000 0.2348
-9.250 -0.4687 0.08296 0.07826 -0.0312 1.0000 0.2508
-9.000 -0.4493 0.08156 0.07688 -0.0284 1.0000 0.2682
-8.750 -0.4271 0.08050 0.07583 -0.0254 1.0000 0.2878
-7.500 -0.7311 0.04410 0.03683 -0.0173 0.9876 0.0883
-7.250 -0.6990 0.04127 0.03296 -0.0178 0.9776 0.0785
-7.000 -0.6595 0.03729 0.02878 -0.0208 0.9719 0.0772
-6.750 -0.6255 0.03537 0.02644 -0.0223 0.9624 0.0782
-6.500 -0.5874 0.03297 0.02376 -0.0244 0.9551 0.0790
-6.250 -0.5453 0.03034 0.02103 -0.0272 0.9485 0.0803
-6.000 -0.4966 0.02842 0.01914 -0.0313 0.9443 0.0849
-5.750 -0.4610 0.02721 0.01782 -0.0326 0.9349 0.0894
-5.500 -0.4124 0.02535 0.01607 -0.0364 0.9306 0.0953
-5.250 -0.3725 0.02419 0.01498 -0.0387 0.9236 0.1034
-5.000 -0.3420 0.02298 0.01393 -0.0395 0.9150 0.1125
-4.750 -0.3151 0.02204 0.01299 -0.0395 0.9068 0.1239
-4.500 -0.2945 0.02110 0.01209 -0.0386 0.8970 0.1419
-4.250 -0.2853 0.01967 0.01111 -0.0359 0.8865 0.2024
-4.000 -0.2927 0.01875 0.01191 -0.0285 0.8769 0.5791
-3.750 -0.2791 0.01968 0.01289 -0.0240 0.8661 0.6336
-3.500 -0.2464 0.02033 0.01353 -0.0229 0.8604 0.6693
-3.250 -0.2249 0.02091 0.01409 -0.0205 0.8518 0.6927
-3.000 -0.1972 0.02136 0.01449 -0.0190 0.8449 0.7166
-2.750 -0.1569 0.02220 0.01537 -0.0184 0.8403 0.7415
-2.500 -0.1368 0.02266 0.01581 -0.0160 0.8308 0.7575
-2.250 -0.1103 0.02255 0.01557 -0.0156 0.8252 0.7696
-2.000 -0.0869 0.02266 0.01562 -0.0149 0.8171 0.7751
-1.750 -0.0628 0.02249 0.01536 -0.0145 0.8102 0.7825
-1.500 -0.0365 0.02232 0.01508 -0.0145 0.8045 0.7892
-1.250 -0.0172 0.02247 0.01520 -0.0134 0.7961 0.7955
-1.000 0.0057 0.02224 0.01487 -0.0129 0.7906 0.8043
-0.750 0.0300 0.02247 0.01509 -0.0125 0.7833 0.8101
-0.500 0.0521 0.02249 0.01506 -0.0118 0.7765 0.8182
-0.250 0.0842 0.02238 0.01488 -0.0124 0.7721 0.8252
0.000 0.0992 0.02277 0.01530 -0.0108 0.7633 0.8337
0.250 0.1259 0.02276 0.01525 -0.0107 0.7576 0.8424
0.500 0.1636 0.02275 0.01519 -0.0122 0.7534 0.8492
0.750 0.1726 0.02324 0.01574 -0.0099 0.7439 0.8603
1.000 0.2115 0.02325 0.01573 -0.0116 0.7391 0.8681
1.250 0.2341 0.02361 0.01610 -0.0112 0.7322 0.8784
1.500 0.2641 0.02388 0.01640 -0.0120 0.7248 0.8883
1.750 0.3088 0.02380 0.01629 -0.0146 0.7204 0.8962
2.000 0.3281 0.02441 0.01697 -0.0141 0.7109 0.9098
2.250 0.3829 0.02427 0.01683 -0.0186 0.7047 0.9147
2.500 0.4146 0.02452 0.01711 -0.0196 0.6954 0.9271
2.750 0.4730 0.02410 0.01669 -0.0245 0.6870 0.9315
3.000 0.5089 0.02427 0.01691 -0.0264 0.6765 0.9434
3.250 0.5662 0.02380 0.01643 -0.0312 0.6685 0.9484
3.500 0.6055 0.02396 0.01667 -0.0339 0.6572 0.9603
3.750 0.6598 0.02334 0.01602 -0.0381 0.6495 0.9681
4.000 0.7037 0.02332 0.01611 -0.0419 0.6365 0.9796
4.250 0.7526 0.02301 0.01587 -0.0461 0.6247 0.9903
4.500 0.8073 0.02222 0.01506 -0.0508 0.6140 0.9999
4.750 0.8096 0.02222 0.01512 -0.0473 0.6023 1.0000
5.000 0.8159 0.02211 0.01502 -0.0440 0.5917 1.0000
5.250 0.8347 0.02160 0.01445 -0.0420 0.5820 1.0000
5.500 0.8434 0.02158 0.01447 -0.0387 0.5686 1.0000
5.750 0.8579 0.02142 0.01432 -0.0361 0.5550 1.0000
6.000 0.8758 0.02117 0.01407 -0.0339 0.5407 1.0000
6.250 0.8944 0.02090 0.01378 -0.0317 0.5248 1.0000
6.500 0.9122 0.02068 0.01355 -0.0294 0.5069 1.0000
6.750 0.9299 0.02048 0.01332 -0.0271 0.4870 1.0000
7.000 0.9489 0.02029 0.01303 -0.0250 0.4658 1.0000
7.250 0.9597 0.02043 0.01319 -0.0218 0.4402 1.0000
7.500 0.9735 0.02056 0.01320 -0.0191 0.4148 1.0000
7.750 0.9854 0.02089 0.01340 -0.0161 0.3890 1.0000
8.000 0.9968 0.02140 0.01377 -0.0133 0.3646 1.0000
8.250 1.0087 0.02206 0.01425 -0.0106 0.3424 1.0000
8.500 1.0222 0.02282 0.01481 -0.0084 0.3221 1.0000
8.750 1.0330 0.02363 0.01557 -0.0057 0.3030 1.0000
9.000 1.0434 0.02445 0.01631 -0.0032 0.2851 1.0000
9.250 1.0533 0.02528 0.01706 -0.0006 0.2683 1.0000
9.500 1.0623 0.02613 0.01785 0.0020 0.2526 1.0000
9.750 1.0708 0.02700 0.01868 0.0046 0.2380 1.0000
10.000 1.0793 0.02792 0.01953 0.0072 0.2244 1.0000
10.250 1.0879 0.02885 0.02036 0.0097 0.2115 1.0000
10.500 1.0881 0.02974 0.02135 0.0133 0.1999 1.0000
10.750 1.0912 0.03080 0.02245 0.0162 0.1881 1.0000
11.000 1.0945 0.03193 0.02357 0.0189 0.1764 1.0000
11.250 1.0987 0.03314 0.02470 0.0211 0.1648 1.0000
11.500 1.0984 0.03447 0.02606 0.0236 0.1535 1.0000
11.750 1.0980 0.03604 0.02771 0.0259 0.1422 1.0000
12.000 1.0983 0.03775 0.02943 0.0277 0.1313 1.0000
12.250 1.1020 0.03948 0.03108 0.0293 0.1213 1.0000
12.500 1.1064 0.04120 0.03278 0.0306 0.1126 1.0000
12.750 1.1103 0.04328 0.03499 0.0319 0.1050 1.0000
13.000 1.1253 0.04486 0.03637 0.0326 0.0980 1.0000
13.250 1.1238 0.04719 0.03900 0.0339 0.0933 1.0000
13.500 1.1375 0.04882 0.04055 0.0346 0.0884 1.0000
13.750 1.1460 0.05125 0.04314 0.0354 0.0847 1.0000
14.000 1.1441 0.05387 0.04600 0.0363 0.0818 1.0000
14.250 1.1492 0.05603 0.04823 0.0368 0.0788 1.0000
14.500 1.1666 0.05828 0.05041 0.0372 0.0756 1.0000
14.750 1.1538 0.06184 0.05430 0.0378 0.0745 1.0000
15.000 1.1400 0.06574 0.05850 0.0379 0.0734 1.0000
15.250 1.1241 0.06995 0.06297 0.0377 0.0724 1.0000
15.500 1.1068 0.07455 0.06781 0.0369 0.0715 1.0000
15.750 1.0865 0.07969 0.07319 0.0356 0.0709 1.0000
16.000 1.0531 0.08692 0.08070 0.0330 0.0712 1.0000
16.250 1.0052 0.09698 0.09107 0.0282 0.0725 1.0000
16.500 0.9533 0.10932 0.10365 0.0215 0.0743 1.0000
16.750 0.9015 0.12365 0.11809 0.0136 0.0758 1.0000
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Polar data table (+)
Polar graphs
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