KC-135 BL52.44 AIRFOIL (kc135a-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: KC-135 BL52.44 AIRFOIL (kc135a-il) Reynolds number: 100,000 Max Cl/Cd: 47.48 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135a-il-100000-n5.txt Download as CSV file: xf-kc135a-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5556 0.09058 0.08498 -0.0468 1.0000 0.0346
-12.250 -0.5793 0.08313 0.07746 -0.0513 1.0000 0.0343
-12.000 -0.6067 0.07639 0.07061 -0.0550 1.0000 0.0341
-11.750 -0.6312 0.07099 0.06508 -0.0572 1.0000 0.0339
-11.500 -0.6543 0.06645 0.06039 -0.0582 1.0000 0.0338
-11.250 -0.6753 0.06263 0.05641 -0.0580 1.0000 0.0337
-11.000 -0.6944 0.05940 0.05302 -0.0565 1.0000 0.0336
-10.750 -0.7122 0.05669 0.05014 -0.0537 1.0000 0.0337
-10.500 -0.7287 0.05431 0.04759 -0.0499 1.0000 0.0337
-10.250 -0.7408 0.05189 0.04496 -0.0462 1.0000 0.0339
-10.000 -0.7486 0.04943 0.04228 -0.0427 1.0000 0.0340
-9.750 -0.7535 0.04704 0.03964 -0.0392 1.0000 0.0341
-9.500 -0.7551 0.04479 0.03715 -0.0358 1.0000 0.0342
-9.250 -0.7545 0.04269 0.03479 -0.0325 1.0000 0.0344
-9.000 -0.7530 0.04071 0.03256 -0.0290 1.0000 0.0347
-8.750 -0.7499 0.03893 0.03054 -0.0257 0.9995 0.0350
-8.500 -0.7196 0.03623 0.02743 -0.0274 0.9875 0.0356
-8.250 -0.6866 0.03445 0.02559 -0.0296 0.9762 0.0368
-8.000 -0.6531 0.03281 0.02382 -0.0316 0.9645 0.0383
-7.750 -0.6183 0.03113 0.02188 -0.0334 0.9534 0.0403
-7.500 -0.5803 0.02934 0.01982 -0.0355 0.9437 0.0418
-7.250 -0.5449 0.02784 0.01835 -0.0375 0.9312 0.0433
-7.000 -0.5102 0.02668 0.01714 -0.0392 0.9185 0.0460
-6.750 -0.4748 0.02558 0.01586 -0.0407 0.9062 0.0491
-6.500 -0.4424 0.02437 0.01475 -0.0420 0.8937 0.0515
-6.250 -0.4150 0.02353 0.01386 -0.0422 0.8791 0.0551
-6.000 -0.3911 0.02271 0.01297 -0.0417 0.8650 0.0585
-5.750 -0.3707 0.02197 0.01222 -0.0407 0.8516 0.0621
-5.500 -0.3495 0.02139 0.01151 -0.0397 0.8398 0.0666
-5.250 -0.3329 0.02072 0.01080 -0.0379 0.8275 0.0711
-5.000 -0.3137 0.02021 0.01018 -0.0365 0.8166 0.0773
-4.750 -0.2944 0.01960 0.00952 -0.0351 0.8071 0.0858
-4.500 -0.2759 0.01904 0.00894 -0.0336 0.7969 0.0983
-4.250 -0.2584 0.01822 0.00824 -0.0320 0.7889 0.1360
-4.000 -0.2658 0.01615 0.00784 -0.0267 0.7793 0.4460
-3.750 -0.2467 0.01617 0.00799 -0.0245 0.7723 0.5314
-3.500 -0.2256 0.01630 0.00808 -0.0228 0.7641 0.5680
-3.250 -0.2026 0.01643 0.00813 -0.0214 0.7569 0.5955
-3.000 -0.1796 0.01660 0.00827 -0.0200 0.7499 0.6205
-2.750 -0.1573 0.01675 0.00838 -0.0184 0.7427 0.6436
-2.500 -0.1317 0.01686 0.00842 -0.0175 0.7372 0.6607
-2.250 -0.1059 0.01687 0.00841 -0.0169 0.7303 0.6696
-2.000 -0.0798 0.01680 0.00822 -0.0166 0.7238 0.6758
-1.750 -0.0527 0.01674 0.00801 -0.0164 0.7186 0.6817
-1.500 -0.0267 0.01672 0.00798 -0.0161 0.7115 0.6868
-1.250 -0.0001 0.01668 0.00786 -0.0159 0.7060 0.6928
-1.000 0.0273 0.01665 0.00771 -0.0158 0.7014 0.6992
-0.750 0.0530 0.01667 0.00775 -0.0155 0.6946 0.7048
-0.500 0.0794 0.01666 0.00769 -0.0153 0.6890 0.7116
-0.250 0.1074 0.01665 0.00761 -0.0152 0.6846 0.7179
0.000 0.1329 0.01671 0.00770 -0.0149 0.6783 0.7245
0.250 0.1587 0.01673 0.00769 -0.0146 0.6726 0.7327
0.500 0.1874 0.01674 0.00769 -0.0146 0.6679 0.7391
0.750 0.2129 0.01681 0.00778 -0.0143 0.6620 0.7474
1.000 0.2394 0.01687 0.00787 -0.0141 0.6559 0.7554
1.250 0.2675 0.01689 0.00789 -0.0141 0.6510 0.7646
1.500 0.2941 0.01698 0.00803 -0.0139 0.6451 0.7736
1.750 0.3201 0.01706 0.00816 -0.0136 0.6388 0.7842
2.000 0.3494 0.01710 0.00823 -0.0138 0.6337 0.7944
2.250 0.3756 0.01720 0.00841 -0.0135 0.6274 0.8066
2.500 0.4025 0.01727 0.00855 -0.0133 0.6204 0.8196
2.750 0.4332 0.01725 0.00856 -0.0136 0.6137 0.8324
3.000 0.4605 0.01730 0.00872 -0.0135 0.6036 0.8473
3.250 0.4920 0.01729 0.00874 -0.0140 0.5950 0.8628
3.500 0.5237 0.01735 0.00888 -0.0147 0.5856 0.8788
3.750 0.5577 0.01742 0.00901 -0.0158 0.5772 0.8948
4.000 0.5927 0.01747 0.00912 -0.0172 0.5677 0.9107
4.250 0.6279 0.01758 0.00932 -0.0188 0.5577 0.9265
4.500 0.6668 0.01759 0.00933 -0.0209 0.5483 0.9396
4.750 0.7032 0.01773 0.00959 -0.0229 0.5358 0.9535
5.000 0.7400 0.01782 0.00975 -0.0249 0.5231 0.9669
5.250 0.7772 0.01790 0.00989 -0.0270 0.5093 0.9800
5.500 0.8150 0.01798 0.01002 -0.0293 0.4931 0.9925
5.750 0.8447 0.01809 0.01018 -0.0302 0.4761 1.0000
6.000 0.8582 0.01824 0.01034 -0.0277 0.4601 1.0000
6.250 0.8717 0.01842 0.01052 -0.0252 0.4419 1.0000
6.500 0.8850 0.01864 0.01071 -0.0227 0.4211 1.0000
6.750 0.8977 0.01891 0.01093 -0.0201 0.3979 1.0000
7.000 0.9094 0.01926 0.01118 -0.0174 0.3735 1.0000
7.250 0.9199 0.01971 0.01151 -0.0145 0.3500 1.0000
7.500 0.9292 0.02025 0.01194 -0.0115 0.3276 1.0000
7.750 0.9376 0.02086 0.01243 -0.0084 0.3076 1.0000
8.000 0.9459 0.02151 0.01300 -0.0054 0.2900 1.0000
8.250 0.9538 0.02218 0.01361 -0.0025 0.2741 1.0000
8.500 0.9612 0.02289 0.01426 0.0005 0.2598 1.0000
8.750 0.9674 0.02358 0.01493 0.0037 0.2468 1.0000
9.000 0.9733 0.02432 0.01566 0.0067 0.2349 1.0000
9.250 0.9790 0.02514 0.01644 0.0096 0.2235 1.0000
9.500 0.9839 0.02606 0.01730 0.0123 0.2121 1.0000
9.750 0.9902 0.02699 0.01826 0.0146 0.1997 1.0000
10.000 0.9963 0.02801 0.01929 0.0167 0.1879 1.0000
10.250 1.0019 0.02913 0.02040 0.0187 0.1771 1.0000
10.500 1.0068 0.03036 0.02163 0.0204 0.1670 1.0000
10.750 1.0139 0.03157 0.02291 0.0219 0.1565 1.0000
11.000 1.0196 0.03292 0.02428 0.0232 0.1471 1.0000
11.250 1.0239 0.03443 0.02579 0.0245 0.1383 1.0000
11.500 1.0301 0.03590 0.02735 0.0255 0.1287 1.0000
11.750 1.0343 0.03757 0.02904 0.0264 0.1205 1.0000
12.000 1.0370 0.03942 0.03091 0.0273 0.1119 1.0000
12.250 1.0411 0.04125 0.03282 0.0280 0.1034 1.0000
12.500 1.0424 0.04335 0.03492 0.0286 0.0966 1.0000
12.750 1.0441 0.04552 0.03715 0.0291 0.0893 1.0000
13.000 1.0451 0.04780 0.03949 0.0295 0.0832 1.0000
13.250 1.0443 0.05032 0.04204 0.0298 0.0777 1.0000
13.500 1.0445 0.05282 0.04460 0.0300 0.0730 1.0000
13.750 1.0434 0.05553 0.04737 0.0300 0.0687 1.0000
14.000 1.0412 0.05843 0.05029 0.0299 0.0654 1.0000
14.250 1.0416 0.06115 0.05314 0.0298 0.0621 1.0000
14.500 1.0395 0.06424 0.05629 0.0294 0.0593 1.0000
14.750 1.0371 0.06742 0.05949 0.0289 0.0570 1.0000
15.000 1.0369 0.07048 0.06271 0.0284 0.0546 1.0000
15.250 1.0356 0.07373 0.06605 0.0277 0.0526 1.0000
15.500 1.0338 0.07708 0.06946 0.0269 0.0510 1.0000
15.750 1.0328 0.08033 0.07273 0.0261 0.0497 1.0000
16.000 1.0305 0.08404 0.07663 0.0251 0.0480 1.0000
16.250 1.0270 0.08796 0.08069 0.0238 0.0464 1.0000
16.500 1.0248 0.09170 0.08453 0.0225 0.0453 1.0000
16.750 1.0224 0.09551 0.08842 0.0211 0.0441 1.0000
17.000 1.0234 0.09872 0.09164 0.0201 0.0431 1.0000
17.250 1.0166 0.10356 0.09667 0.0181 0.0422 1.0000
17.500 1.0068 0.10908 0.10240 0.0156 0.0413 1.0000
17.750 0.9961 0.11494 0.10845 0.0127 0.0407 1.0000
18.000 0.9833 0.12138 0.11507 0.0094 0.0400 1.0000
18.250 0.9675 0.12867 0.12254 0.0054 0.0395 1.0000
18.500 0.9445 0.13784 0.13190 0.0002 0.0391 1.0000
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Polar data table (+)
Polar graphs
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