KC-135 BL200.76 AIRFOIL (kc135c-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: KC-135 BL200.76 AIRFOIL (kc135c-il) Reynolds number: 50,000 Max Cl/Cd: 34.24 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-kc135c-il-50000-n5.txt Download as CSV file: xf-kc135c-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: KC-135 BL200.76 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4873 0.10329 0.09638 -0.0257 1.0000 0.1353
-9.250 -0.4845 0.09944 0.09260 -0.0259 1.0000 0.1427
-9.000 -0.4988 0.09615 0.08943 -0.0290 1.0000 0.1512
-8.750 -0.4876 0.09248 0.08579 -0.0274 1.0000 0.1606
-8.500 -0.5218 0.08924 0.08272 -0.0318 1.0000 0.1668
-8.000 -0.5127 0.08260 0.07623 -0.0288 1.0000 0.1932
-7.000 -0.5364 0.06419 0.05693 -0.0335 1.0000 0.0761
-6.750 -0.5346 0.06101 0.05331 -0.0309 1.0000 0.0628
-6.500 -0.5287 0.05737 0.04972 -0.0291 1.0000 0.0603
-6.250 -0.5260 0.05445 0.04664 -0.0266 1.0000 0.0580
-6.000 -0.5228 0.05179 0.04375 -0.0238 1.0000 0.0558
-5.750 -0.5185 0.04928 0.04089 -0.0209 1.0000 0.0536
-5.500 -0.5124 0.04699 0.03830 -0.0181 1.0000 0.0533
-5.250 -0.5043 0.04492 0.03595 -0.0156 1.0000 0.0536
-5.000 -0.4948 0.04290 0.03365 -0.0134 1.0000 0.0546
-4.750 -0.4833 0.04091 0.03135 -0.0112 1.0000 0.0552
-4.500 -0.4661 0.03883 0.02888 -0.0097 0.9988 0.0544
-4.250 -0.4334 0.03645 0.02601 -0.0107 0.9922 0.0537
-4.000 -0.3996 0.03433 0.02347 -0.0119 0.9863 0.0537
-3.750 -0.3671 0.03254 0.02134 -0.0129 0.9799 0.0551
-3.500 -0.3334 0.03106 0.01956 -0.0140 0.9739 0.0589
-3.250 -0.2984 0.02969 0.01793 -0.0150 0.9682 0.0609
-3.000 -0.2623 0.02849 0.01653 -0.0160 0.9634 0.0625
-2.750 -0.2299 0.02729 0.01527 -0.0166 0.9576 0.0662
-2.500 -0.1956 0.02639 0.01427 -0.0179 0.9525 0.0729
-2.250 -0.1687 0.02569 0.01337 -0.0179 0.9450 0.0772
-2.000 -0.1378 0.02481 0.01242 -0.0191 0.9391 0.0867
-1.750 -0.1122 0.02419 0.01165 -0.0192 0.9315 0.0984
-1.500 -0.0819 0.02346 0.01091 -0.0202 0.9253 0.1239
-1.250 -0.0755 0.02090 0.01101 -0.0161 0.9187 0.6935
-1.000 0.0777 0.02208 0.01224 -0.0325 0.9353 0.9782
-0.750 0.1207 0.02200 0.01193 -0.0366 0.9287 0.9872
-0.500 0.1693 0.02192 0.01164 -0.0417 0.9242 0.9951
-0.250 0.2018 0.02190 0.01150 -0.0440 0.9160 1.0000
0.000 0.2336 0.02190 0.01138 -0.0458 0.9089 1.0000
0.250 0.2511 0.02200 0.01141 -0.0450 0.8982 1.0000
0.500 0.2740 0.02209 0.01144 -0.0450 0.8895 1.0000
0.750 0.2983 0.02219 0.01149 -0.0452 0.8810 1.0000
1.000 0.3151 0.02239 0.01165 -0.0439 0.8709 1.0000
1.250 0.3461 0.02247 0.01170 -0.0450 0.8640 1.0000
1.500 0.3613 0.02274 0.01195 -0.0433 0.8530 1.0000
1.750 0.3823 0.02298 0.01218 -0.0425 0.8434 1.0000
2.000 0.4127 0.02309 0.01233 -0.0432 0.8353 1.0000
2.250 0.4324 0.02331 0.01256 -0.0419 0.8232 1.0000
2.500 0.4585 0.02333 0.01261 -0.0413 0.8096 1.0000
2.750 0.4872 0.02318 0.01250 -0.0407 0.7939 1.0000
3.000 0.5146 0.02300 0.01241 -0.0398 0.7779 1.0000
3.250 0.5396 0.02289 0.01237 -0.0386 0.7625 1.0000
3.500 0.5625 0.02289 0.01245 -0.0371 0.7479 1.0000
3.750 0.5850 0.02292 0.01261 -0.0357 0.7334 1.0000
4.000 0.6082 0.02290 0.01271 -0.0343 0.7184 1.0000
4.250 0.6309 0.02287 0.01281 -0.0327 0.7020 1.0000
4.500 0.6496 0.02296 0.01303 -0.0306 0.6827 1.0000
4.750 0.6711 0.02290 0.01312 -0.0287 0.6622 1.0000
5.000 0.6913 0.02285 0.01326 -0.0266 0.6388 1.0000
5.250 0.7119 0.02275 0.01331 -0.0245 0.6118 1.0000
5.500 0.7305 0.02273 0.01343 -0.0221 0.5787 1.0000
5.750 0.7503 0.02268 0.01346 -0.0198 0.5387 1.0000
6.000 0.7695 0.02274 0.01355 -0.0174 0.4904 1.0000
6.250 0.7883 0.02302 0.01362 -0.0150 0.4383 1.0000
6.500 0.8035 0.02370 0.01405 -0.0125 0.3886 1.0000
6.750 0.8131 0.02470 0.01469 -0.0096 0.3357 1.0000
7.000 0.8198 0.02587 0.01554 -0.0067 0.2836 1.0000
7.250 0.8279 0.02704 0.01656 -0.0041 0.2402 1.0000
7.500 0.8364 0.02827 0.01769 -0.0018 0.2002 1.0000
7.750 0.8436 0.02965 0.01895 0.0007 0.1558 1.0000
8.000 0.8497 0.03131 0.02033 0.0031 0.1205 1.0000
8.250 0.8565 0.03304 0.02187 0.0054 0.0976 1.0000
8.500 0.8670 0.03474 0.02355 0.0075 0.0854 1.0000
8.750 0.8804 0.03643 0.02534 0.0091 0.0754 1.0000
9.000 0.8955 0.03819 0.02716 0.0105 0.0678 1.0000
9.250 0.9160 0.04008 0.02923 0.0114 0.0622 1.0000
9.500 0.9349 0.04217 0.03140 0.0122 0.0572 1.0000
9.750 0.9531 0.04436 0.03393 0.0132 0.0528 1.0000
10.000 0.9705 0.04683 0.03665 0.0140 0.0502 1.0000
10.250 0.9866 0.04974 0.03961 0.0146 0.0476 1.0000
10.500 0.9893 0.05243 0.04278 0.0167 0.0460 1.0000
10.750 0.9876 0.05539 0.04614 0.0189 0.0444 1.0000
11.000 0.9832 0.05853 0.04961 0.0207 0.0434 1.0000
11.250 0.9751 0.06196 0.05335 0.0222 0.0428 1.0000
11.500 0.9633 0.06578 0.05745 0.0231 0.0424 1.0000
11.750 0.9479 0.07003 0.06197 0.0233 0.0423 1.0000
12.000 0.9293 0.07490 0.06707 0.0226 0.0424 1.0000
12.250 0.9077 0.08054 0.07292 0.0207 0.0426 1.0000
12.500 0.8836 0.08719 0.07974 0.0174 0.0430 1.0000
12.750 0.8576 0.09519 0.08788 0.0127 0.0436 1.0000
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Polar data table (+)
Polar graphs
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