KC-135 BL200.76 AIRFOIL (kc135c-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: KC-135 BL200.76 AIRFOIL (kc135c-il) Reynolds number: 200,000 Max Cl/Cd: 71.4 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-kc135c-il-200000.txt Download as CSV file: xf-kc135c-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4670 0.08826 0.08472 -0.0324 1.0000 0.0352
-9.000 -0.4710 0.08375 0.08026 -0.0355 1.0000 0.0358
-8.750 -0.4790 0.07892 0.07546 -0.0395 1.0000 0.0357
-8.500 -0.4930 0.07490 0.07145 -0.0416 1.0000 0.0362
-8.250 -0.5066 0.07178 0.06830 -0.0409 1.0000 0.0365
-8.000 -0.5152 0.06862 0.06509 -0.0403 1.0000 0.0372
-7.750 -0.5218 0.06590 0.06225 -0.0389 1.0000 0.0381
-7.500 -0.5287 0.06504 0.06114 -0.0360 1.0000 0.0393
-7.250 -0.5361 0.06421 0.06010 -0.0321 1.0000 0.0397
-7.000 -0.5455 0.06301 0.05877 -0.0275 1.0000 0.0398
-6.750 -0.5567 0.06188 0.05753 -0.0226 1.0000 0.0399
-6.500 -0.5485 0.05273 0.04842 -0.0249 0.9963 0.0414
-6.250 -0.5233 0.04864 0.04434 -0.0278 0.9913 0.0433
-6.000 -0.4942 0.04538 0.04089 -0.0305 0.9856 0.0468
-5.750 -0.4561 0.04703 0.04169 -0.0312 0.9771 0.0526
-5.500 -0.4354 0.03878 0.03345 -0.0341 0.9725 0.0551
-5.250 -0.4067 0.03577 0.03037 -0.0360 0.9669 0.0583
-4.750 -0.3418 0.03060 0.02459 -0.0394 0.9570 0.0721
-4.500 -0.3136 0.02883 0.02246 -0.0400 0.9496 0.0841
-4.250 -0.2823 0.02656 0.02010 -0.0418 0.9449 0.1005
-3.750 -0.1826 0.00736 0.00036 -0.0444 0.9215 0.0700
-3.250 -0.1307 0.01857 0.01073 -0.0438 0.9260 0.0503
-3.000 -0.1024 0.01765 0.00971 -0.0435 0.9179 0.0514
-2.750 -0.0691 0.01650 0.00849 -0.0442 0.9131 0.0519
-2.500 -0.0445 0.01554 0.00751 -0.0434 0.9046 0.0534
-2.250 -0.0195 0.01449 0.00653 -0.0429 0.8985 0.0588
-2.000 0.0025 0.01403 0.00605 -0.0417 0.8900 0.0642
-1.750 0.0261 0.01337 0.00534 -0.0408 0.8838 0.0711
-1.500 0.0478 0.01301 0.00493 -0.0396 0.8755 0.0871
-1.250 0.0529 0.01090 0.00450 -0.0358 0.8687 0.5526
-1.000 0.0597 0.01051 0.00497 -0.0300 0.8601 0.7826
-0.750 0.0826 0.01054 0.00508 -0.0278 0.8549 0.8352
-0.500 0.1057 0.01068 0.00526 -0.0261 0.8481 0.8687
-0.250 0.1336 0.01083 0.00539 -0.0252 0.8424 0.8949
0.000 0.1700 0.01107 0.00560 -0.0259 0.8381 0.9173
0.250 0.2041 0.01121 0.00570 -0.0271 0.8311 0.9291
0.500 0.2425 0.01120 0.00561 -0.0291 0.8252 0.9357
0.750 0.2775 0.01123 0.00560 -0.0306 0.8156 0.9437
1.000 0.3175 0.01117 0.00548 -0.0329 0.8054 0.9492
1.250 0.3541 0.01108 0.00531 -0.0344 0.7941 0.9569
1.500 0.3959 0.01103 0.00523 -0.0373 0.7833 0.9622
1.750 0.4328 0.01104 0.00526 -0.0394 0.7749 0.9709
2.000 0.4756 0.01099 0.00518 -0.0426 0.7673 0.9765
2.250 0.5148 0.01096 0.00519 -0.0453 0.7575 0.9848
2.500 0.5569 0.01087 0.00513 -0.0485 0.7477 0.9918
2.750 0.5991 0.01074 0.00500 -0.0516 0.7376 0.9987
3.000 0.6203 0.01066 0.00495 -0.0507 0.7258 1.0000
3.250 0.6377 0.01061 0.00492 -0.0489 0.7138 1.0000
3.500 0.6561 0.01059 0.00493 -0.0471 0.7007 1.0000
3.750 0.6752 0.01058 0.00493 -0.0454 0.6863 1.0000
4.000 0.6946 0.01057 0.00494 -0.0436 0.6702 1.0000
4.250 0.7145 0.01056 0.00494 -0.0419 0.6520 1.0000
4.500 0.7336 0.01056 0.00499 -0.0400 0.6270 1.0000
4.750 0.7516 0.01058 0.00494 -0.0378 0.5901 1.0000
5.000 0.7675 0.01075 0.00494 -0.0353 0.5307 1.0000
5.250 0.7784 0.01132 0.00504 -0.0319 0.4386 1.0000
5.500 0.7882 0.01216 0.00543 -0.0288 0.3604 1.0000
5.750 0.8017 0.01288 0.00592 -0.0264 0.3118 1.0000
6.000 0.8170 0.01352 0.00639 -0.0243 0.2763 1.0000
6.250 0.8332 0.01411 0.00687 -0.0225 0.2424 1.0000
6.500 0.8485 0.01477 0.00738 -0.0205 0.2061 1.0000
6.750 0.8600 0.01576 0.00797 -0.0180 0.1257 1.0000
7.000 0.8656 0.01737 0.00910 -0.0145 0.0709 1.0000
7.250 0.8773 0.01848 0.01017 -0.0119 0.0587 1.0000
7.500 0.8912 0.01942 0.01115 -0.0097 0.0514 1.0000
7.750 0.9024 0.02063 0.01238 -0.0072 0.0465 1.0000
8.000 0.9168 0.02167 0.01349 -0.0051 0.0430 1.0000
8.250 0.9304 0.02297 0.01477 -0.0031 0.0399 1.0000
8.500 0.9468 0.02478 0.01664 -0.0016 0.0370 1.0000
8.750 0.9664 0.02604 0.01803 -0.0004 0.0348 1.0000
9.000 0.9875 0.02766 0.01978 0.0005 0.0331 1.0000
9.250 1.0085 0.02944 0.02170 0.0014 0.0319 1.0000
9.500 1.0289 0.03153 0.02395 0.0022 0.0309 1.0000
9.750 1.0480 0.03406 0.02664 0.0029 0.0298 1.0000
10.000 1.0593 0.03878 0.03171 0.0041 0.0286 1.0000
10.250 1.0664 0.04081 0.03407 0.0066 0.0283 1.0000
10.500 1.0702 0.04381 0.03741 0.0092 0.0282 1.0000
10.750 1.0706 0.04809 0.04200 0.0115 0.0285 1.0000
11.000 1.0720 0.05138 0.04555 0.0138 0.0289 1.0000
11.250 1.0697 0.05283 0.04722 0.0171 0.0292 1.0000
11.500 1.0597 0.05423 0.04890 0.0212 0.0298 1.0000
11.750 1.0107 0.05888 0.05417 0.0261 0.0320 1.0000
12.000 0.9795 0.06413 0.05974 0.0271 0.0334 1.0000
12.250 0.9536 0.06936 0.06517 0.0266 0.0341 1.0000
12.500 0.9277 0.07516 0.07115 0.0248 0.0347 1.0000
12.750 0.9031 0.08153 0.07766 0.0218 0.0353 1.0000
13.000 0.8762 0.08921 0.08545 0.0172 0.0357 1.0000
13.250 0.8482 0.09856 0.09491 0.0108 0.0361 1.0000
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Polar data table (+)
Polar graphs
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