KC-135 BL52.44 AIRFOIL (kc135a-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: KC-135 BL52.44 AIRFOIL (kc135a-il) Reynolds number: 200,000 Max Cl/Cd: 68.88 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135a-il-200000.txt Download as CSV file: xf-kc135a-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5242 0.10097 0.09718 -0.0452 1.0000 0.0668
-12.000 -0.5660 0.09250 0.08864 -0.0522 1.0000 0.0669
-11.750 -0.5990 0.08694 0.08299 -0.0557 1.0000 0.0670
-11.500 -0.6288 0.08269 0.07865 -0.0571 1.0000 0.0670
-11.250 -0.6570 0.07943 0.07531 -0.0566 1.0000 0.0670
-11.000 -0.6927 0.07775 0.07351 -0.0529 1.0000 0.0671
-10.750 -0.6254 0.06919 0.06526 -0.0575 1.0000 0.0699
-10.500 -0.6418 0.06616 0.06217 -0.0564 1.0000 0.0704
-10.250 -0.6572 0.06365 0.05962 -0.0541 1.0000 0.0711
-10.000 -0.6754 0.06154 0.05746 -0.0503 1.0000 0.0718
-9.750 -0.6886 0.05934 0.05518 -0.0469 1.0000 0.0730
-9.500 -0.7024 0.05740 0.05311 -0.0430 1.0000 0.0749
-9.250 -0.7395 0.05911 0.05438 -0.0345 1.0000 0.0780
-9.000 -0.7655 0.06014 0.05521 -0.0268 1.0000 0.0784
-8.750 -0.7447 0.05122 0.04647 -0.0302 0.9962 0.0809
-8.500 -0.7119 0.04780 0.04304 -0.0335 0.9887 0.0839
-8.250 -0.6963 0.03698 0.03039 -0.0310 0.9755 0.0484
-8.000 -0.6626 0.03358 0.02674 -0.0332 0.9674 0.0478
-7.750 -0.6254 0.03056 0.02343 -0.0356 0.9606 0.0474
-7.500 -0.5885 0.02791 0.02051 -0.0376 0.9510 0.0469
-7.250 -0.5466 0.02568 0.01803 -0.0403 0.9441 0.0473
-7.000 -0.5094 0.02406 0.01619 -0.0420 0.9317 0.0482
-6.750 -0.4707 0.02224 0.01426 -0.0442 0.9204 0.0499
-6.500 -0.4344 0.02102 0.01308 -0.0461 0.9082 0.0527
-6.250 -0.4035 0.02016 0.01212 -0.0466 0.8939 0.0558
-6.000 -0.3775 0.01915 0.01103 -0.0461 0.8791 0.0584
-5.750 -0.3562 0.01831 0.01025 -0.0451 0.8652 0.0621
-5.500 -0.3344 0.01781 0.00966 -0.0440 0.8529 0.0661
-5.250 -0.3172 0.01700 0.00882 -0.0421 0.8417 0.0703
-5.000 -0.2993 0.01652 0.00832 -0.0404 0.8299 0.0754
-4.750 -0.2822 0.01594 0.00768 -0.0384 0.8200 0.0811
-4.500 -0.2640 0.01547 0.00718 -0.0367 0.8100 0.0890
-4.250 -0.2463 0.01494 0.00662 -0.0349 0.8012 0.1014
-4.000 -0.2334 0.01400 0.00594 -0.0324 0.7926 0.1585
-3.750 -0.2437 0.01226 0.00580 -0.0258 0.7845 0.5254
-3.500 -0.2238 0.01251 0.00606 -0.0236 0.7765 0.5768
-3.250 -0.2001 0.01272 0.00622 -0.0223 0.7699 0.6022
-3.000 -0.1766 0.01287 0.00635 -0.0211 0.7617 0.6207
-2.750 -0.1511 0.01301 0.00643 -0.0202 0.7554 0.6366
-2.500 -0.1266 0.01315 0.00657 -0.0192 0.7486 0.6523
-2.250 -0.1017 0.01325 0.00665 -0.0183 0.7420 0.6667
-2.000 -0.0760 0.01338 0.00667 -0.0176 0.7368 0.6802
-1.750 -0.0504 0.01343 0.00680 -0.0169 0.7297 0.6912
-1.500 -0.0245 0.01343 0.00673 -0.0164 0.7236 0.7000
-1.250 0.0040 0.01343 0.00665 -0.0164 0.7190 0.7054
-1.000 0.0292 0.01341 0.00664 -0.0161 0.7123 0.7115
-0.750 0.0559 0.01338 0.00655 -0.0159 0.7065 0.7175
-0.500 0.0845 0.01338 0.00650 -0.0159 0.7020 0.7232
-0.250 0.1097 0.01340 0.00653 -0.0156 0.6956 0.7299
0.000 0.1364 0.01337 0.00648 -0.0154 0.6898 0.7360
0.250 0.1648 0.01338 0.00646 -0.0154 0.6852 0.7427
0.500 0.1897 0.01344 0.00652 -0.0150 0.6792 0.7507
0.750 0.2167 0.01342 0.00656 -0.0148 0.6734 0.7572
1.000 0.2444 0.01344 0.00654 -0.0147 0.6688 0.7654
1.250 0.2708 0.01349 0.00663 -0.0145 0.6634 0.7735
1.500 0.2962 0.01352 0.00672 -0.0140 0.6572 0.7830
1.750 0.3241 0.01349 0.00670 -0.0139 0.6519 0.7921
2.000 0.3495 0.01349 0.00673 -0.0134 0.6445 0.8033
2.250 0.3763 0.01338 0.00668 -0.0129 0.6364 0.8141
2.500 0.4039 0.01335 0.00666 -0.0127 0.6299 0.8268
2.750 0.4290 0.01334 0.00677 -0.0121 0.6225 0.8416
3.000 0.4578 0.01331 0.00675 -0.0120 0.6166 0.8575
3.250 0.4855 0.01334 0.00690 -0.0119 0.6093 0.8750
3.500 0.5175 0.01335 0.00696 -0.0125 0.6021 0.8928
3.750 0.5531 0.01340 0.00706 -0.0139 0.5951 0.9101
4.000 0.5911 0.01345 0.00718 -0.0159 0.5864 0.9257
4.250 0.6339 0.01352 0.00726 -0.0188 0.5777 0.9376
4.500 0.6763 0.01354 0.00730 -0.0217 0.5677 0.9492
4.750 0.7179 0.01360 0.00742 -0.0245 0.5567 0.9605
5.000 0.7618 0.01361 0.00742 -0.0278 0.5452 0.9699
5.250 0.8068 0.01359 0.00739 -0.0313 0.5318 0.9787
5.500 0.8511 0.01356 0.00741 -0.0349 0.5159 0.9882
5.750 0.8964 0.01354 0.00742 -0.0388 0.4973 0.9972
6.000 0.9197 0.01353 0.00744 -0.0384 0.4792 1.0000
6.250 0.9319 0.01359 0.00750 -0.0357 0.4607 1.0000
6.500 0.9444 0.01371 0.00759 -0.0330 0.4387 1.0000
6.750 0.9563 0.01391 0.00773 -0.0302 0.4120 1.0000
7.000 0.9665 0.01425 0.00792 -0.0270 0.3818 1.0000
7.250 0.9747 0.01475 0.00823 -0.0236 0.3523 1.0000
7.500 0.9826 0.01533 0.00866 -0.0202 0.3253 1.0000
7.750 0.9908 0.01594 0.00914 -0.0170 0.3019 1.0000
8.000 0.9987 0.01657 0.00964 -0.0137 0.2807 1.0000
8.250 1.0059 0.01721 0.01017 -0.0104 0.2621 1.0000
8.500 1.0133 0.01783 0.01071 -0.0071 0.2459 1.0000
8.750 1.0211 0.01844 0.01127 -0.0040 0.2316 1.0000
9.000 1.0272 0.01902 0.01183 -0.0005 0.2196 1.0000
9.250 1.0316 0.01967 0.01243 0.0031 0.2091 1.0000
9.500 1.0375 0.02034 0.01307 0.0062 0.1984 1.0000
9.750 1.0456 0.02100 0.01378 0.0089 0.1879 1.0000
10.000 1.0520 0.02183 0.01457 0.0115 0.1783 1.0000
10.250 1.0593 0.02266 0.01542 0.0138 0.1685 1.0000
10.500 1.0675 0.02353 0.01633 0.0158 0.1585 1.0000
10.750 1.0733 0.02461 0.01739 0.0178 0.1493 1.0000
11.000 1.0794 0.02573 0.01853 0.0196 0.1392 1.0000
11.250 1.0862 0.02692 0.01976 0.0211 0.1287 1.0000
11.500 1.0905 0.02834 0.02119 0.0226 0.1176 1.0000
11.750 1.0931 0.03000 0.02282 0.0240 0.1069 1.0000
12.000 1.0936 0.03189 0.02468 0.0253 0.0960 1.0000
12.250 1.0924 0.03402 0.02674 0.0265 0.0870 1.0000
12.500 1.0952 0.03593 0.02869 0.0275 0.0789 1.0000
12.750 1.0957 0.03806 0.03082 0.0284 0.0729 1.0000
13.000 1.0979 0.04009 0.03286 0.0292 0.0684 1.0000
13.250 1.0996 0.04221 0.03499 0.0300 0.0645 1.0000
13.500 1.1038 0.04417 0.03701 0.0306 0.0611 1.0000
13.750 1.1063 0.04627 0.03907 0.0312 0.0585 1.0000
14.000 1.1111 0.04825 0.04112 0.0318 0.0560 1.0000
14.250 1.1165 0.05022 0.04318 0.0322 0.0538 1.0000
14.500 1.1207 0.05230 0.04528 0.0325 0.0517 1.0000
14.750 1.1290 0.05398 0.04688 0.0333 0.0497 1.0000
15.000 1.1318 0.05638 0.04946 0.0333 0.0481 1.0000
15.250 1.1373 0.05851 0.05170 0.0336 0.0467 1.0000
15.500 1.1415 0.06077 0.05402 0.0335 0.0451 1.0000
15.750 1.1501 0.06254 0.05575 0.0339 0.0437 1.0000
16.000 1.1583 0.06456 0.05783 0.0344 0.0425 1.0000
16.250 1.1568 0.06765 0.06113 0.0340 0.0416 1.0000
16.500 1.1573 0.07057 0.06421 0.0336 0.0407 1.0000
16.750 1.1563 0.07374 0.06752 0.0330 0.0398 1.0000
17.000 1.1564 0.07680 0.07068 0.0323 0.0389 1.0000
17.250 1.1609 0.07923 0.07311 0.0319 0.0378 1.0000
17.500 1.1690 0.08148 0.07537 0.0323 0.0367 1.0000
17.750 1.1584 0.08612 0.08024 0.0306 0.0365 1.0000
18.000 1.1455 0.09126 0.08561 0.0286 0.0362 1.0000
18.250 1.1300 0.09701 0.09160 0.0260 0.0359 1.0000
18.500 1.1140 0.10308 0.09788 0.0231 0.0358 1.0000
18.750 1.0926 0.11034 0.10538 0.0193 0.0356 1.0000
19.000 1.0697 0.11823 0.11350 0.0149 0.0356 1.0000
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