KC-135 BL351.6 AIRFOIL (kc135d-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: KC-135 BL351.6 AIRFOIL (kc135d-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.12 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135d-il-1000000-n5.txt Download as CSV file: xf-kc135d-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4579 0.08339 0.08179 -0.0279 1.0000 0.0041
-8.500 -0.4614 0.07913 0.07756 -0.0305 1.0000 0.0040
-8.250 -0.4700 0.07485 0.07331 -0.0338 1.0000 0.0040
-7.750 -0.4681 0.06408 0.06244 -0.0439 0.9802 0.0038
-7.500 -0.4463 0.05709 0.05530 -0.0520 0.9640 0.0037
-7.250 -0.4258 0.05063 0.04861 -0.0574 0.9415 0.0036
-7.000 -0.4144 0.04582 0.04354 -0.0582 0.9149 0.0037
-6.750 -0.4049 0.04167 0.03913 -0.0573 0.8946 0.0039
-6.500 -0.3948 0.03724 0.03441 -0.0557 0.8782 0.0041
-6.250 -0.3868 0.03094 0.02767 -0.0530 0.8642 0.0047
-6.000 -0.3758 0.02513 0.02136 -0.0501 0.8525 0.0049
-5.500 -0.3471 0.01297 0.00785 -0.0445 0.8339 0.0068
-5.250 -0.3240 0.01167 0.00630 -0.0437 0.8260 0.0073
-5.000 -0.2994 0.01096 0.00546 -0.0431 0.8177 0.0077
-4.750 -0.2734 0.01075 0.00520 -0.0428 0.8099 0.0082
-4.500 -0.2471 0.01056 0.00495 -0.0426 0.8019 0.0086
-4.250 -0.2212 0.01028 0.00460 -0.0423 0.7949 0.0092
-4.000 -0.1955 0.00993 0.00418 -0.0419 0.7878 0.0100
-3.750 -0.1691 0.00979 0.00398 -0.0417 0.7811 0.0106
-3.500 -0.1440 0.00935 0.00348 -0.0412 0.7739 0.0115
-3.250 -0.1175 0.00922 0.00332 -0.0410 0.7674 0.0122
-3.000 -0.0911 0.00901 0.00308 -0.0408 0.7610 0.0129
-2.500 -0.0381 0.00867 0.00266 -0.0404 0.7491 0.0147
-2.250 -0.0116 0.00852 0.00246 -0.0401 0.7427 0.0152
-2.000 0.0147 0.00832 0.00222 -0.0399 0.7364 0.0154
-1.750 0.0397 0.00793 0.00174 -0.0393 0.7284 0.0165
-1.500 0.0662 0.00778 0.00156 -0.0391 0.7196 0.0178
-1.250 0.0927 0.00767 0.00141 -0.0389 0.7094 0.0188
-1.000 0.1191 0.00759 0.00127 -0.0386 0.6969 0.0202
-0.750 0.1457 0.00752 0.00114 -0.0384 0.6838 0.0213
-0.500 0.1726 0.00746 0.00105 -0.0382 0.6720 0.0223
-0.250 0.1995 0.00739 0.00093 -0.0380 0.6617 0.0245
0.000 0.2263 0.00734 0.00086 -0.0379 0.6517 0.0293
0.250 0.2533 0.00731 0.00081 -0.0377 0.6410 0.0354
0.500 0.2700 0.00585 0.00070 -0.0363 0.6315 0.5460
0.750 0.2945 0.00565 0.00072 -0.0357 0.6197 0.6324
1.000 0.3194 0.00554 0.00074 -0.0352 0.6057 0.6857
1.250 0.3447 0.00547 0.00076 -0.0347 0.5922 0.7266
1.500 0.3690 0.00539 0.00080 -0.0339 0.5762 0.7770
1.750 0.3921 0.00530 0.00086 -0.0329 0.5581 0.8382
2.000 0.4157 0.00525 0.00094 -0.0319 0.5386 0.8949
2.250 0.4423 0.00538 0.00102 -0.0316 0.5054 0.9207
2.500 0.4710 0.00566 0.00115 -0.0320 0.4564 0.9419
2.750 0.5032 0.00597 0.00129 -0.0333 0.4116 0.9571
3.000 0.5348 0.00640 0.00147 -0.0345 0.3461 0.9680
3.250 0.5652 0.00691 0.00169 -0.0356 0.2822 0.9763
3.500 0.5976 0.00721 0.00186 -0.0369 0.2474 0.9813
4.000 0.6588 0.00773 0.00218 -0.0387 0.2006 0.9908
4.250 0.6886 0.00801 0.00238 -0.0395 0.1764 0.9950
4.500 0.7191 0.00835 0.00258 -0.0405 0.1462 0.9986
4.750 0.7445 0.00885 0.00286 -0.0405 0.1014 1.0000
5.000 0.7637 0.00939 0.00319 -0.0390 0.0599 1.0000
5.500 0.8058 0.01020 0.00383 -0.0368 0.0228 1.0000
5.750 0.8288 0.01045 0.00408 -0.0359 0.0200 1.0000
6.000 0.8513 0.01074 0.00436 -0.0351 0.0172 1.0000
6.250 0.8739 0.01102 0.00467 -0.0342 0.0147 1.0000
6.500 0.8969 0.01129 0.00496 -0.0334 0.0128 1.0000
6.750 0.9189 0.01164 0.00531 -0.0325 0.0106 1.0000
7.000 0.9413 0.01198 0.00567 -0.0316 0.0094 1.0000
7.250 0.9637 0.01232 0.00604 -0.0308 0.0086 1.0000
7.500 0.9858 0.01268 0.00643 -0.0300 0.0079 1.0000
7.750 1.0075 0.01310 0.00688 -0.0290 0.0073 1.0000
8.000 1.0277 0.01367 0.00751 -0.0278 0.0066 1.0000
8.250 1.0488 0.01413 0.00803 -0.0269 0.0064 1.0000
8.500 1.0699 0.01460 0.00856 -0.0259 0.0063 1.0000
8.750 1.0903 0.01511 0.00914 -0.0248 0.0061 1.0000
9.000 1.1112 0.01556 0.00965 -0.0239 0.0057 1.0000
9.250 1.1310 0.01609 0.01025 -0.0228 0.0055 1.0000
9.500 1.1504 0.01665 0.01087 -0.0216 0.0052 1.0000
9.750 1.1686 0.01729 0.01158 -0.0203 0.0050 1.0000
10.000 1.1867 0.01790 0.01225 -0.0190 0.0048 1.0000
10.250 1.2033 0.01862 0.01304 -0.0175 0.0047 1.0000
10.500 1.2183 0.01943 0.01393 -0.0158 0.0045 1.0000
10.750 1.2306 0.02039 0.01501 -0.0137 0.0043 1.0000
11.000 1.2366 0.02156 0.01631 -0.0106 0.0042 1.0000
11.250 1.2413 0.02276 0.01765 -0.0074 0.0041 1.0000
11.500 1.2486 0.02383 0.01883 -0.0048 0.0041 1.0000
11.750 1.2595 0.02466 0.01975 -0.0028 0.0040 1.0000
12.000 1.2668 0.02578 0.02099 -0.0006 0.0040 1.0000
12.250 1.2707 0.02724 0.02258 0.0017 0.0039 1.0000
12.500 1.2782 0.02843 0.02389 0.0035 0.0038 1.0000
12.750 1.2802 0.03015 0.02576 0.0055 0.0038 1.0000
13.000 1.2816 0.03200 0.02775 0.0072 0.0038 1.0000
13.250 1.2931 0.03295 0.02878 0.0080 0.0036 1.0000
13.500 1.2920 0.03518 0.03116 0.0094 0.0035 1.0000
13.750 1.2921 0.03739 0.03351 0.0104 0.0035 1.0000
14.000 1.2887 0.04009 0.03638 0.0112 0.0034 1.0000
14.250 1.2801 0.04352 0.03997 0.0117 0.0034 1.0000
14.500 1.2865 0.04537 0.04190 0.0115 0.0032 1.0000
14.750 1.2703 0.05009 0.04682 0.0111 0.0033 1.0000
15.000 1.2711 0.05292 0.04974 0.0104 0.0032 1.0000
15.250 1.2537 0.05845 0.05546 0.0087 0.0031 1.0000
15.500 1.2450 0.06311 0.06025 0.0068 0.0031 1.0000
15.750 1.2293 0.06935 0.06664 0.0038 0.0031 1.0000
16.000 1.2040 0.07788 0.07536 -0.0007 0.0032 1.0000
16.250 1.1883 0.08527 0.08289 -0.0049 0.0031 1.0000
16.500 1.1630 0.09511 0.09289 -0.0105 0.0031 1.0000
16.750 1.1424 0.10411 0.10201 -0.0155 0.0031 1.0000
17.000 1.0967 0.11895 0.11704 -0.0236 0.0033 1.0000
17.250 1.0680 0.13039 0.12857 -0.0297 0.0032 1.0000
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Polar data table (+)
Polar graphs
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