KC-135 BL351.6 AIRFOIL (kc135d-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: KC-135 BL351.6 AIRFOIL (kc135d-il) Reynolds number: 50,000 Max Cl/Cd: 36.59 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135d-il-50000-n5.txt Download as CSV file: xf-kc135d-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4605 0.09582 0.08910 -0.0265 1.0000 0.1133
-8.000 -0.4668 0.08915 0.08263 -0.0286 1.0000 0.1259
-7.750 -0.4780 0.08609 0.07965 -0.0315 1.0000 0.1303
-7.500 -0.4748 0.08249 0.07613 -0.0307 1.0000 0.1389
-7.250 -0.4959 0.08053 0.07413 -0.0342 1.0000 0.1468
-5.250 -0.4440 0.05262 0.04516 -0.0287 1.0000 0.0839
-5.000 -0.4264 0.05011 0.04189 -0.0263 1.0000 0.0596
-4.750 -0.4167 0.04668 0.03843 -0.0248 1.0000 0.0570
-4.500 -0.4048 0.04400 0.03550 -0.0230 1.0000 0.0544
-4.250 -0.3911 0.04164 0.03281 -0.0213 1.0000 0.0541
-4.000 -0.3759 0.03958 0.03040 -0.0197 1.0000 0.0548
-3.750 -0.3592 0.03757 0.02802 -0.0181 1.0000 0.0554
-3.500 -0.3408 0.03555 0.02563 -0.0166 1.0000 0.0545
-3.250 -0.3076 0.03331 0.02293 -0.0176 0.9948 0.0535
-3.000 -0.2733 0.03131 0.02045 -0.0186 0.9892 0.0534
-2.750 -0.2391 0.02982 0.01856 -0.0197 0.9834 0.0569
-2.500 -0.2034 0.02846 0.01681 -0.0208 0.9781 0.0591
-2.250 -0.1701 0.02724 0.01535 -0.0214 0.9725 0.0600
-2.000 -0.1353 0.02592 0.01396 -0.0223 0.9679 0.0618
-1.750 -0.1035 0.02503 0.01295 -0.0233 0.9619 0.0686
-1.500 -0.0712 0.02441 0.01209 -0.0242 0.9559 0.0732
-1.250 -0.0419 0.02374 0.01127 -0.0249 0.9490 0.0773
-1.000 -0.0096 0.02324 0.01058 -0.0261 0.9425 0.0864
-0.750 0.0212 0.02274 0.01006 -0.0272 0.9359 0.1073
-0.500 0.0951 0.01969 0.00999 -0.0345 0.9407 1.0000
-0.250 0.1228 0.01989 0.00984 -0.0350 0.9318 1.0000
0.000 0.1585 0.02012 0.00974 -0.0371 0.9253 1.0000
0.250 0.1856 0.02035 0.00978 -0.0376 0.9162 1.0000
0.500 0.2172 0.02059 0.00985 -0.0388 0.9086 1.0000
0.750 0.2493 0.02083 0.00994 -0.0401 0.9006 1.0000
1.000 0.2781 0.02109 0.01010 -0.0408 0.8918 1.0000
1.250 0.3137 0.02130 0.01024 -0.0426 0.8846 1.0000
1.500 0.3388 0.02158 0.01049 -0.0425 0.8744 1.0000
1.750 0.3695 0.02182 0.01072 -0.0433 0.8659 1.0000
2.000 0.4000 0.02206 0.01097 -0.0440 0.8570 1.0000
2.250 0.4266 0.02230 0.01124 -0.0439 0.8457 1.0000
2.500 0.4586 0.02233 0.01131 -0.0443 0.8320 1.0000
2.750 0.4931 0.02214 0.01122 -0.0447 0.8154 1.0000
3.000 0.5265 0.02190 0.01106 -0.0447 0.7987 1.0000
3.250 0.5561 0.02179 0.01104 -0.0442 0.7832 1.0000
3.500 0.5803 0.02183 0.01124 -0.0430 0.7667 1.0000
3.750 0.6046 0.02186 0.01141 -0.0418 0.7499 1.0000
4.000 0.6296 0.02185 0.01155 -0.0406 0.7322 1.0000
4.250 0.6559 0.02175 0.01160 -0.0394 0.7135 1.0000
4.500 0.6786 0.02174 0.01182 -0.0378 0.6917 1.0000
4.750 0.7033 0.02161 0.01186 -0.0362 0.6677 1.0000
5.000 0.7249 0.02158 0.01201 -0.0343 0.6384 1.0000
5.250 0.7459 0.02159 0.01218 -0.0322 0.6030 1.0000
5.500 0.7675 0.02159 0.01230 -0.0301 0.5598 1.0000
5.750 0.7884 0.02171 0.01248 -0.0279 0.5065 1.0000
6.000 0.8083 0.02209 0.01269 -0.0256 0.4483 1.0000
6.250 0.8247 0.02288 0.01322 -0.0232 0.3920 1.0000
6.500 0.8343 0.02403 0.01392 -0.0204 0.3255 1.0000
6.750 0.8415 0.02538 0.01485 -0.0177 0.2588 1.0000
7.000 0.8516 0.02668 0.01600 -0.0155 0.2018 1.0000
7.250 0.8605 0.02829 0.01731 -0.0133 0.1337 1.0000
7.500 0.8696 0.03030 0.01898 -0.0111 0.0953 1.0000
7.750 0.8808 0.03224 0.02074 -0.0092 0.0772 1.0000
8.000 0.8939 0.03413 0.02261 -0.0075 0.0660 1.0000
8.250 0.9129 0.03591 0.02468 -0.0061 0.0595 1.0000
8.500 0.9291 0.03796 0.02671 -0.0049 0.0533 1.0000
8.750 0.9510 0.04001 0.02919 -0.0039 0.0484 1.0000
9.000 0.9726 0.04246 0.03190 -0.0031 0.0457 1.0000
9.250 0.9916 0.04520 0.03480 -0.0023 0.0434 1.0000
9.500 1.0056 0.04831 0.03826 -0.0011 0.0412 1.0000
9.750 1.0129 0.05124 0.04170 0.0007 0.0393 1.0000
10.000 1.0162 0.05440 0.04528 0.0026 0.0379 1.0000
10.250 1.0147 0.05775 0.04901 0.0047 0.0374 1.0000
10.500 1.0073 0.06113 0.05272 0.0070 0.0371 1.0000
10.750 0.9958 0.06474 0.05662 0.0089 0.0370 1.0000
11.000 0.9810 0.06867 0.06081 0.0100 0.0370 1.0000
11.250 0.9634 0.07308 0.06547 0.0100 0.0370 1.0000
11.500 0.9437 0.07813 0.07071 0.0089 0.0373 1.0000
11.750 0.9217 0.08410 0.07686 0.0063 0.0376 1.0000
12.000 0.8992 0.09105 0.08394 0.0024 0.0380 1.0000
12.250 0.8765 0.09928 0.09225 -0.0028 0.0385 1.0000
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Polar data table (+)
Polar graphs
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