KC-135 BL351.6 AIRFOIL (kc135d-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: KC-135 BL351.6 AIRFOIL (kc135d-il) Reynolds number: 200,000 Max Cl/Cd: 68.77 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135d-il-200000-n5.txt Download as CSV file: xf-kc135d-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3526 0.08590 0.08254 -0.0276 1.0000 0.0182
-9.000 -0.3533 0.08191 0.07858 -0.0288 1.0000 0.0185
-8.750 -0.3547 0.07793 0.07463 -0.0301 1.0000 0.0188
-8.500 -0.3572 0.07387 0.07061 -0.0315 1.0000 0.0192
-8.250 -0.3608 0.06976 0.06654 -0.0330 1.0000 0.0193
-8.000 -0.3663 0.06560 0.06242 -0.0348 1.0000 0.0193
-7.750 -0.3759 0.06143 0.05830 -0.0371 1.0000 0.0193
-7.500 -0.3917 0.05782 0.05473 -0.0383 1.0000 0.0189
-7.250 -0.4037 0.05445 0.05137 -0.0378 1.0000 0.0187
-7.000 -0.4074 0.05057 0.04745 -0.0386 0.9962 0.0195
-6.750 -0.3861 0.04660 0.04310 -0.0441 0.9845 0.0223
-6.500 -0.3683 0.04206 0.03832 -0.0465 0.9755 0.0225
-6.250 -0.3503 0.03730 0.03332 -0.0483 0.9670 0.0226
-6.000 -0.3325 0.03282 0.02863 -0.0494 0.9575 0.0226
-5.750 -0.3134 0.02851 0.02409 -0.0504 0.9488 0.0226
-4.500 -0.2368 0.02557 0.01918 -0.0492 0.9271 0.0164
-4.250 -0.2107 0.02458 0.01807 -0.0495 0.9183 0.0187
-4.000 -0.1817 0.02254 0.01567 -0.0494 0.9116 0.0196
-3.750 -0.1549 0.02061 0.01338 -0.0487 0.9028 0.0200
-3.500 -0.1263 0.01898 0.01144 -0.0484 0.8957 0.0208
-3.250 -0.0983 0.01848 0.01065 -0.0480 0.8875 0.0226
-3.000 -0.0721 0.01653 0.00860 -0.0477 0.8804 0.0246
-2.750 -0.0457 0.01557 0.00754 -0.0473 0.8727 0.0256
-2.500 -0.0196 0.01477 0.00665 -0.0468 0.8651 0.0269
-2.250 0.0063 0.01425 0.00607 -0.0464 0.8577 0.0298
-2.000 0.0314 0.01365 0.00541 -0.0458 0.8505 0.0311
-1.750 0.0562 0.01311 0.00482 -0.0451 0.8432 0.0321
-1.500 0.0810 0.01269 0.00433 -0.0444 0.8359 0.0331
-1.250 0.1048 0.01215 0.00372 -0.0437 0.8290 0.0353
-1.000 0.1302 0.01187 0.00339 -0.0433 0.8222 0.0408
-0.750 0.1561 0.01167 0.00310 -0.0428 0.8151 0.0445
-0.500 0.1821 0.01149 0.00284 -0.0424 0.8085 0.0520
-0.250 0.1943 0.00966 0.00270 -0.0401 0.8009 0.5792
0.000 0.2110 0.00899 0.00281 -0.0371 0.7937 0.7834
0.250 0.2443 0.00884 0.00287 -0.0375 0.7864 0.8797
0.500 0.3039 0.00887 0.00293 -0.0435 0.7778 0.9567
0.750 0.3401 0.00888 0.00282 -0.0452 0.7637 0.9692
1.000 0.3746 0.00889 0.00274 -0.0466 0.7488 0.9786
1.250 0.4097 0.00891 0.00269 -0.0482 0.7373 0.9870
1.500 0.4457 0.00894 0.00265 -0.0501 0.7262 0.9946
1.750 0.4783 0.00897 0.00265 -0.0514 0.7136 1.0000
2.000 0.5010 0.00902 0.00267 -0.0504 0.7013 1.0000
2.250 0.5240 0.00909 0.00273 -0.0494 0.6892 1.0000
2.500 0.5472 0.00916 0.00279 -0.0485 0.6766 1.0000
2.750 0.5704 0.00925 0.00286 -0.0476 0.6627 1.0000
3.000 0.5936 0.00934 0.00294 -0.0467 0.6467 1.0000
3.250 0.6167 0.00945 0.00306 -0.0457 0.6287 1.0000
3.500 0.6396 0.00958 0.00317 -0.0447 0.6075 1.0000
3.750 0.6619 0.00973 0.00328 -0.0436 0.5804 1.0000
4.000 0.6836 0.00994 0.00341 -0.0423 0.5443 1.0000
4.250 0.7034 0.01027 0.00359 -0.0407 0.4913 1.0000
4.500 0.7205 0.01081 0.00383 -0.0387 0.4263 1.0000
4.750 0.7360 0.01154 0.00420 -0.0366 0.3497 1.0000
5.000 0.7514 0.01236 0.00465 -0.0347 0.2860 1.0000
5.250 0.7693 0.01303 0.00508 -0.0332 0.2366 1.0000
5.500 0.7893 0.01356 0.00552 -0.0320 0.2052 1.0000
5.750 0.8100 0.01405 0.00595 -0.0310 0.1768 1.0000
6.000 0.8288 0.01473 0.00643 -0.0297 0.1302 1.0000
6.250 0.8434 0.01586 0.00715 -0.0279 0.0630 1.0000
6.500 0.8603 0.01684 0.00797 -0.0263 0.0381 1.0000
6.750 0.8790 0.01765 0.00883 -0.0249 0.0305 1.0000
7.000 0.8982 0.01838 0.00965 -0.0236 0.0258 1.0000
7.250 0.9147 0.01938 0.01073 -0.0220 0.0222 1.0000
7.500 0.9326 0.02021 0.01170 -0.0205 0.0207 1.0000
7.750 0.9491 0.02117 0.01278 -0.0188 0.0192 1.0000
8.000 0.9646 0.02225 0.01399 -0.0171 0.0179 1.0000
8.250 0.9801 0.02335 0.01518 -0.0154 0.0169 1.0000
8.500 0.9934 0.02477 0.01667 -0.0136 0.0156 1.0000
8.750 1.0075 0.02642 0.01842 -0.0119 0.0147 1.0000
9.000 1.0245 0.02763 0.01980 -0.0106 0.0141 1.0000
9.250 1.0409 0.02916 0.02151 -0.0091 0.0135 1.0000
9.500 1.0564 0.03090 0.02346 -0.0077 0.0130 1.0000
9.750 1.0706 0.03280 0.02561 -0.0062 0.0126 1.0000
10.000 1.0825 0.03483 0.02789 -0.0044 0.0122 1.0000
10.250 1.0913 0.03701 0.03034 -0.0024 0.0120 1.0000
10.500 1.0957 0.03922 0.03281 0.0002 0.0118 1.0000
10.750 1.0968 0.04130 0.03513 0.0028 0.0115 1.0000
11.000 1.0943 0.04384 0.03794 0.0055 0.0114 1.0000
11.250 1.0927 0.04559 0.03984 0.0076 0.0109 1.0000
11.500 1.0873 0.04813 0.04260 0.0095 0.0108 1.0000
11.750 1.0838 0.05032 0.04487 0.0107 0.0103 1.0000
12.000 1.0734 0.05371 0.04847 0.0117 0.0102 1.0000
12.250 1.0604 0.05760 0.05258 0.0121 0.0102 1.0000
12.500 1.0446 0.06209 0.05726 0.0117 0.0100 1.0000
12.750 1.0300 0.06672 0.06211 0.0105 0.0101 1.0000
13.000 1.0138 0.07201 0.06762 0.0085 0.0101 1.0000
13.250 0.9974 0.07787 0.07365 0.0054 0.0101 1.0000
13.500 0.9778 0.08506 0.08103 0.0011 0.0101 1.0000
13.750 0.9588 0.09314 0.08927 -0.0042 0.0101 1.0000
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Polar data table (+)
Polar graphs
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