KC-135 BL351.6 AIRFOIL (kc135d-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: KC-135 BL351.6 AIRFOIL (kc135d-il) Reynolds number: 100,000 Max Cl/Cd: 54.68 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135d-il-100000.txt Download as CSV file: xf-kc135d-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: KC-135 BL351.6 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4711 0.09630 0.09149 -0.0364 1.0000 0.0592
-8.500 -0.4827 0.09377 0.08894 -0.0387 1.0000 0.0594
-8.250 -0.4896 0.09128 0.08639 -0.0400 1.0000 0.0595
-8.000 -0.4551 0.08349 0.07883 -0.0333 1.0000 0.0645
-7.750 -0.4591 0.08014 0.07551 -0.0345 1.0000 0.0659
-7.500 -0.4617 0.07677 0.07216 -0.0356 1.0000 0.0677
-7.250 -0.4647 0.07360 0.06898 -0.0366 1.0000 0.0697
-7.000 -0.4702 0.07119 0.06646 -0.0375 1.0000 0.0723
-6.750 -0.4816 0.07155 0.06639 -0.0366 1.0000 0.0737
-6.500 -0.4749 0.06452 0.05968 -0.0355 1.0000 0.0757
-6.250 -0.4712 0.06145 0.05669 -0.0333 1.0000 0.0785
-6.000 -0.4711 0.05908 0.05428 -0.0311 1.0000 0.0823
-5.500 -0.4726 0.05434 0.04921 -0.0269 1.0000 0.0907
-5.250 -0.4684 0.05180 0.04666 -0.0247 1.0000 0.0960
-5.000 -0.4649 0.04974 0.04429 -0.0230 1.0000 0.1046
-4.750 -0.4586 0.04886 0.04304 -0.0210 1.0000 0.1173
-4.500 -0.4502 0.04464 0.03909 -0.0196 1.0000 0.1235
-4.250 -0.4414 0.04242 0.03674 -0.0182 1.0000 0.1393
-4.000 -0.4335 0.04005 0.03430 -0.0168 1.0000 0.1652
-3.500 -0.4187 0.03544 0.02974 -0.0134 1.0000 0.2485
-3.250 -0.4066 0.03361 0.02780 -0.0117 1.0000 0.2881
-3.000 -0.3872 0.03087 0.02520 -0.0109 0.9983 0.3252
-2.750 -0.3491 0.02836 0.02238 -0.0132 0.9937 0.3404
-2.500 -0.2713 0.02761 0.01969 -0.0169 0.9885 0.1534
-2.250 -0.2215 0.02668 0.01784 -0.0173 0.9839 0.1012
-2.000 -0.1849 0.02506 0.01587 -0.0178 0.9788 0.0865
-1.750 -0.1480 0.02339 0.01405 -0.0191 0.9740 0.0809
-1.500 -0.1077 0.02238 0.01290 -0.0212 0.9699 0.0811
-1.250 -0.0779 0.02162 0.01209 -0.0215 0.9632 0.0844
-1.000 -0.0421 0.02089 0.01138 -0.0230 0.9580 0.0858
-0.750 -0.0128 0.02034 0.01079 -0.0234 0.9514 0.0897
-0.500 0.0202 0.01993 0.01035 -0.0247 0.9449 0.1033
-0.250 0.1011 0.01678 0.01012 -0.0340 0.9480 1.0000
0.000 0.1448 0.01707 0.00999 -0.0374 0.9422 1.0000
0.250 0.1720 0.01732 0.01004 -0.0379 0.9328 1.0000
0.500 0.2178 0.01756 0.01013 -0.0419 0.9275 1.0000
0.750 0.2416 0.01783 0.01029 -0.0416 0.9176 1.0000
1.000 0.2804 0.01808 0.01046 -0.0442 0.9112 1.0000
1.250 0.3117 0.01832 0.01065 -0.0453 0.9024 1.0000
1.500 0.3518 0.01838 0.01069 -0.0477 0.8921 1.0000
1.750 0.4117 0.01790 0.01023 -0.0531 0.8797 1.0000
2.000 0.4613 0.01742 0.00979 -0.0563 0.8676 1.0000
2.250 0.5010 0.01716 0.00960 -0.0578 0.8575 1.0000
2.500 0.5268 0.01720 0.00968 -0.0571 0.8453 1.0000
2.750 0.5538 0.01718 0.00971 -0.0564 0.8332 1.0000
3.000 0.5814 0.01710 0.00970 -0.0557 0.8210 1.0000
3.250 0.6088 0.01696 0.00964 -0.0548 0.8080 1.0000
3.500 0.6352 0.01680 0.00961 -0.0537 0.7942 1.0000
3.750 0.6608 0.01661 0.00950 -0.0523 0.7789 1.0000
4.000 0.6862 0.01637 0.00936 -0.0507 0.7625 1.0000
4.250 0.7127 0.01603 0.00911 -0.0491 0.7447 1.0000
4.500 0.7347 0.01584 0.00907 -0.0470 0.7223 1.0000
4.750 0.7583 0.01552 0.00885 -0.0449 0.6965 1.0000
5.000 0.7803 0.01524 0.00864 -0.0425 0.6634 1.0000
5.250 0.8011 0.01498 0.00840 -0.0399 0.6178 1.0000
5.500 0.8169 0.01494 0.00820 -0.0364 0.5378 1.0000
5.750 0.8279 0.01558 0.00817 -0.0326 0.4322 1.0000
6.000 0.8404 0.01656 0.00870 -0.0299 0.3584 1.0000
6.250 0.8550 0.01751 0.00939 -0.0278 0.3077 1.0000
6.500 0.8673 0.01856 0.01019 -0.0254 0.2396 1.0000
6.750 0.8689 0.02095 0.01159 -0.0214 0.1104 1.0000
7.000 0.8800 0.02274 0.01315 -0.0187 0.0836 1.0000
7.250 0.8942 0.02438 0.01475 -0.0166 0.0723 1.0000
7.500 0.9114 0.02654 0.01674 -0.0150 0.0652 1.0000
7.750 0.9336 0.02804 0.01844 -0.0138 0.0592 1.0000
8.000 0.9580 0.03045 0.02077 -0.0134 0.0544 1.0000
8.250 0.9855 0.03361 0.02415 -0.0131 0.0526 1.0000
8.500 1.0080 0.03642 0.02740 -0.0120 0.0519 1.0000
8.750 1.0251 0.03937 0.03082 -0.0103 0.0512 1.0000
9.000 1.0370 0.04222 0.03416 -0.0081 0.0499 1.0000
9.250 1.0453 0.04543 0.03784 -0.0058 0.0491 1.0000
9.500 1.0496 0.04935 0.04221 -0.0033 0.0500 1.0000
9.750 1.0500 0.05360 0.04684 -0.0009 0.0512 1.0000
10.000 1.0491 0.05841 0.05192 0.0012 0.0524 1.0000
10.250 1.0429 0.06170 0.05569 0.0043 0.0554 1.0000
10.500 1.0039 0.06609 0.06058 0.0090 0.0580 1.0000
10.750 0.9772 0.07042 0.06513 0.0110 0.0595 1.0000
11.000 0.9516 0.07521 0.07008 0.0112 0.0607 1.0000
11.250 0.9264 0.08067 0.07566 0.0096 0.0616 1.0000
11.500 0.9049 0.08680 0.08188 0.0069 0.0627 1.0000
11.750 0.7689 0.08988 0.08532 0.0047 0.0617 1.0000
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Polar data table (+)
Polar graphs
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