KC-135 BL52.44 AIRFOIL (kc135a-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: KC-135 BL52.44 AIRFOIL (kc135a-il) Reynolds number: 50,000 Max Cl/Cd: 27.74 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135a-il-50000-n5.txt Download as CSV file: xf-kc135a-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5342 0.10009 0.09235 -0.0449 1.0000 0.0572
-12.000 -0.5482 0.09400 0.08625 -0.0481 1.0000 0.0569
-11.750 -0.5658 0.08815 0.08037 -0.0512 1.0000 0.0566
-11.500 -0.5835 0.08292 0.07510 -0.0535 1.0000 0.0561
-11.250 -0.6056 0.07806 0.07015 -0.0553 1.0000 0.0559
-11.000 -0.6267 0.07393 0.06592 -0.0559 1.0000 0.0557
-10.750 -0.6462 0.07044 0.06232 -0.0552 1.0000 0.0555
-10.500 -0.6661 0.06749 0.05925 -0.0531 1.0000 0.0555
-10.250 -0.6841 0.06491 0.05653 -0.0500 1.0000 0.0555
-10.000 -0.6975 0.06225 0.05368 -0.0471 1.0000 0.0557
-9.750 -0.7079 0.05967 0.05088 -0.0440 1.0000 0.0559
-9.500 -0.7150 0.05718 0.04814 -0.0408 1.0000 0.0562
-9.250 -0.7194 0.05479 0.04550 -0.0376 1.0000 0.0564
-9.000 -0.7207 0.05248 0.04293 -0.0344 1.0000 0.0567
-8.750 -0.7190 0.05030 0.04049 -0.0314 1.0000 0.0569
-8.500 -0.7164 0.04827 0.03820 -0.0282 1.0000 0.0572
-8.250 -0.7113 0.04628 0.03608 -0.0254 1.0000 0.0579
-8.000 -0.7041 0.04469 0.03447 -0.0229 1.0000 0.0591
-7.750 -0.6991 0.04337 0.03310 -0.0200 1.0000 0.0603
-7.500 -0.6954 0.04219 0.03180 -0.0168 1.0000 0.0617
-7.250 -0.6618 0.04012 0.02942 -0.0187 0.9909 0.0642
-7.000 -0.6218 0.03813 0.02705 -0.0211 0.9817 0.0665
-6.750 -0.5799 0.03633 0.02528 -0.0239 0.9737 0.0705
-6.500 -0.5374 0.03494 0.02382 -0.0263 0.9652 0.0747
-6.250 -0.4914 0.03365 0.02243 -0.0290 0.9588 0.0801
-6.000 -0.4560 0.03253 0.02132 -0.0306 0.9484 0.0861
-5.750 -0.4232 0.03143 0.02011 -0.0319 0.9381 0.0928
-5.500 -0.3925 0.03023 0.01889 -0.0334 0.9285 0.1012
-5.250 -0.3705 0.02912 0.01773 -0.0334 0.9160 0.1100
-5.000 -0.3485 0.02796 0.01655 -0.0334 0.9046 0.1240
-4.750 -0.3282 0.02648 0.01522 -0.0334 0.8944 0.1511
-4.500 -0.3348 0.02402 0.01452 -0.0292 0.8809 0.3687
-4.250 -0.3224 0.02438 0.01531 -0.0249 0.8702 0.5491
-4.000 -0.3022 0.02491 0.01573 -0.0221 0.8610 0.6046
-3.750 -0.2828 0.02549 0.01624 -0.0191 0.8512 0.6421
-3.500 -0.2529 0.02652 0.01729 -0.0164 0.8442 0.6841
-3.250 -0.2267 0.02726 0.01793 -0.0140 0.8363 0.7148
-3.000 -0.1929 0.02741 0.01792 -0.0143 0.8287 0.7252
-2.750 -0.1718 0.02703 0.01733 -0.0138 0.8210 0.7336
-2.500 -0.1438 0.02697 0.01712 -0.0139 0.8125 0.7388
-2.250 -0.1132 0.02673 0.01669 -0.0146 0.8066 0.7458
-2.000 -0.0959 0.02664 0.01649 -0.0134 0.7972 0.7534
-1.750 -0.0636 0.02655 0.01626 -0.0142 0.7911 0.7595
-1.500 -0.0461 0.02644 0.01604 -0.0131 0.7832 0.7686
-1.250 -0.0153 0.02647 0.01598 -0.0137 0.7764 0.7744
-1.000 0.0161 0.02634 0.01574 -0.0144 0.7713 0.7822
-0.750 0.0335 0.02650 0.01587 -0.0132 0.7625 0.7903
-0.500 0.0630 0.02650 0.01580 -0.0136 0.7568 0.7982
-0.250 0.0863 0.02658 0.01583 -0.0133 0.7502 0.8070
0.000 0.1114 0.02675 0.01599 -0.0131 0.7428 0.8155
0.250 0.1419 0.02675 0.01593 -0.0137 0.7378 0.8247
0.500 0.1643 0.02705 0.01625 -0.0133 0.7300 0.8342
0.750 0.1932 0.02719 0.01638 -0.0138 0.7235 0.8440
1.000 0.2296 0.02720 0.01636 -0.0152 0.7191 0.8535
1.250 0.2510 0.02768 0.01690 -0.0150 0.7099 0.8646
1.500 0.2840 0.02776 0.01698 -0.0161 0.7042 0.8761
1.750 0.3171 0.02810 0.01736 -0.0176 0.6969 0.8867
2.000 0.3508 0.02837 0.01767 -0.0192 0.6895 0.8980
2.250 0.3906 0.02834 0.01765 -0.0212 0.6845 0.9099
2.500 0.4227 0.02892 0.01833 -0.0232 0.6745 0.9221
2.750 0.4677 0.02888 0.01833 -0.0263 0.6683 0.9322
3.000 0.5004 0.02931 0.01886 -0.0283 0.6581 0.9464
3.250 0.5448 0.02910 0.01868 -0.0310 0.6505 0.9582
3.500 0.5808 0.02937 0.01906 -0.0335 0.6383 0.9730
3.750 0.6241 0.02918 0.01893 -0.0364 0.6278 0.9857
4.000 0.6688 0.02892 0.01875 -0.0397 0.6167 0.9990
4.250 0.6686 0.02932 0.01919 -0.0359 0.6052 1.0000
4.500 0.6850 0.02914 0.01899 -0.0337 0.5966 1.0000
4.750 0.6892 0.02949 0.01938 -0.0302 0.5850 1.0000
5.000 0.6972 0.02979 0.01970 -0.0271 0.5735 1.0000
5.250 0.7218 0.02945 0.01936 -0.0258 0.5640 1.0000
5.500 0.7305 0.02979 0.01975 -0.0228 0.5511 1.0000
5.750 0.7409 0.03008 0.02010 -0.0199 0.5379 1.0000
6.000 0.7563 0.03016 0.02022 -0.0176 0.5251 1.0000
6.250 0.7759 0.03004 0.02014 -0.0157 0.5121 1.0000
6.500 0.7962 0.02988 0.02000 -0.0138 0.4983 1.0000
6.750 0.8094 0.03003 0.02022 -0.0112 0.4825 1.0000
7.000 0.8224 0.03019 0.02043 -0.0086 0.4660 1.0000
7.250 0.8324 0.03050 0.02078 -0.0058 0.4483 1.0000
7.500 0.8408 0.03093 0.02126 -0.0029 0.4295 1.0000
7.750 0.8509 0.03130 0.02167 -0.0001 0.4103 1.0000
8.000 0.8644 0.03155 0.02190 0.0023 0.3912 1.0000
8.250 0.8790 0.03177 0.02205 0.0046 0.3725 1.0000
8.500 0.8921 0.03216 0.02234 0.0069 0.3543 1.0000
8.750 0.9009 0.03287 0.02300 0.0095 0.3366 1.0000
9.000 0.9100 0.03368 0.02375 0.0118 0.3198 1.0000
9.250 0.9197 0.03459 0.02459 0.0139 0.3042 1.0000
9.500 0.9292 0.03557 0.02552 0.0159 0.2893 1.0000
9.750 0.9394 0.03662 0.02655 0.0177 0.2754 1.0000
10.000 0.9463 0.03791 0.02787 0.0195 0.2619 1.0000
10.250 0.9535 0.03926 0.02925 0.0211 0.2491 1.0000
10.500 0.9615 0.04061 0.03062 0.0226 0.2370 1.0000
10.750 0.9695 0.04195 0.03194 0.0240 0.2249 1.0000
11.000 0.9757 0.04342 0.03342 0.0253 0.2131 1.0000
11.250 0.9771 0.04533 0.03543 0.0266 0.2018 1.0000
11.500 0.9797 0.04715 0.03729 0.0277 0.1909 1.0000
11.750 0.9843 0.04879 0.03888 0.0287 0.1803 1.0000
12.000 0.9821 0.05117 0.04141 0.0294 0.1701 1.0000
12.250 0.9819 0.05347 0.04380 0.0301 0.1604 1.0000
12.500 0.9855 0.05534 0.04560 0.0307 0.1514 1.0000
12.750 0.9806 0.05838 0.04886 0.0308 0.1426 1.0000
13.000 0.9813 0.06081 0.05131 0.0311 0.1347 1.0000
13.250 0.9786 0.06373 0.05434 0.0311 0.1270 1.0000
13.500 0.9769 0.06671 0.05740 0.0310 0.1203 1.0000
13.750 0.9735 0.06989 0.06067 0.0307 0.1137 1.0000
14.000 0.9707 0.07318 0.06403 0.0303 0.1081 1.0000
14.250 0.9628 0.07738 0.06843 0.0294 0.1031 1.0000
14.500 0.9685 0.07947 0.07041 0.0294 0.0981 1.0000
14.750 0.9498 0.08573 0.07700 0.0272 0.0949 1.0000
15.000 0.9338 0.09176 0.08324 0.0249 0.0918 1.0000
15.250 0.9330 0.09525 0.08676 0.0239 0.0883 1.0000
15.500 0.9226 0.10068 0.09228 0.0218 0.0859 1.0000
15.750 0.8808 0.11276 0.10463 0.0156 0.0853 1.0000
16.000 0.8044 0.13504 0.12700 0.0037 0.0848 1.0000
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