LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il) Reynolds number: 200,000 Max Cl/Cd: 59.56 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141e-il-200000-n5.txt Download as CSV file: xf-c141e-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL761.11 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5402 0.08925 0.08516 -0.0422 1.0000 0.0267
-10.250 -0.5646 0.08150 0.07747 -0.0456 1.0000 0.0269
-10.000 -0.6057 0.07127 0.06732 -0.0520 1.0000 0.0267
-9.750 -0.6557 0.06476 0.06078 -0.0515 1.0000 0.0263
-9.500 -0.7067 0.05724 0.05307 -0.0483 1.0000 0.0263
-9.250 -0.7831 0.04333 0.03836 -0.0424 1.0000 0.0269
-9.000 -0.8001 0.03437 0.02824 -0.0403 0.9975 0.0280
-8.750 -0.7754 0.03303 0.02679 -0.0411 0.9953 0.0285
-8.500 -0.7509 0.03155 0.02513 -0.0417 0.9932 0.0291
-8.250 -0.7279 0.02982 0.02314 -0.0419 0.9905 0.0298
-8.000 -0.7035 0.02799 0.02098 -0.0423 0.9880 0.0308
-7.750 -0.6777 0.02598 0.01848 -0.0428 0.9858 0.0323
-7.500 -0.6489 0.02491 0.01729 -0.0437 0.9842 0.0332
-7.250 -0.6233 0.02414 0.01645 -0.0437 0.9812 0.0340
-7.000 -0.5963 0.02321 0.01538 -0.0440 0.9783 0.0350
-6.750 -0.5677 0.02223 0.01419 -0.0445 0.9760 0.0364
-6.500 -0.5377 0.02130 0.01303 -0.0453 0.9741 0.0379
-6.250 -0.5064 0.02068 0.01243 -0.0464 0.9724 0.0392
-6.000 -0.4802 0.02009 0.01179 -0.0463 0.9691 0.0405
-5.750 -0.4531 0.01944 0.01104 -0.0463 0.9658 0.0421
-5.500 -0.4233 0.01881 0.01030 -0.0469 0.9632 0.0440
-5.250 -0.3922 0.01832 0.00983 -0.0479 0.9610 0.0459
-5.000 -0.3598 0.01784 0.00933 -0.0490 0.9593 0.0483
-4.750 -0.3326 0.01736 0.00877 -0.0490 0.9559 0.0505
-4.500 -0.3067 0.01693 0.00837 -0.0487 0.9516 0.0529
-4.250 -0.2763 0.01658 0.00802 -0.0494 0.9487 0.0564
-4.000 -0.2441 0.01615 0.00758 -0.0505 0.9465 0.0601
-3.750 -0.2106 0.01580 0.00726 -0.0518 0.9448 0.0644
-3.500 -0.1853 0.01552 0.00697 -0.0513 0.9401 0.0692
-3.250 -0.1579 0.01522 0.00671 -0.0513 0.9358 0.0746
-3.000 -0.1261 0.01492 0.00642 -0.0522 0.9329 0.0814
-2.750 -0.0925 0.01462 0.00616 -0.0535 0.9308 0.0897
-2.500 -0.0582 0.01429 0.00589 -0.0549 0.9291 0.0997
-2.250 -0.0368 0.01412 0.00574 -0.0536 0.9222 0.1090
-2.000 -0.0064 0.01384 0.00553 -0.0542 0.9185 0.1233
-1.750 0.0256 0.01349 0.00530 -0.0551 0.9158 0.1463
-1.500 0.0578 0.01297 0.00507 -0.0562 0.9136 0.2083
-1.250 0.0743 0.01200 0.00497 -0.0544 0.9061 0.4276
-1.000 0.0973 0.01116 0.00497 -0.0533 0.9019 0.6457
-0.750 0.1245 0.01074 0.00500 -0.0525 0.8991 0.7637
-0.500 0.1498 0.01064 0.00517 -0.0510 0.8941 0.8477
-0.250 0.1819 0.01067 0.00529 -0.0511 0.8894 0.9015
0.000 0.2206 0.01068 0.00531 -0.0529 0.8862 0.9306
0.250 0.2643 0.01058 0.00520 -0.0557 0.8827 0.9501
0.500 0.3070 0.01057 0.00517 -0.0583 0.8733 0.9716
0.750 0.3591 0.01037 0.00495 -0.0629 0.8643 0.9818
1.000 0.3993 0.01013 0.00467 -0.0651 0.8495 0.9862
1.250 0.4377 0.00996 0.00445 -0.0670 0.8324 0.9908
1.500 0.4747 0.00984 0.00429 -0.0687 0.8131 0.9953
1.750 0.5119 0.00974 0.00410 -0.0704 0.7865 0.9992
2.000 0.5384 0.00970 0.00396 -0.0698 0.7540 1.0000
2.250 0.5617 0.00974 0.00385 -0.0686 0.7153 1.0000
2.500 0.5836 0.00988 0.00378 -0.0671 0.6698 1.0000
2.750 0.6033 0.01013 0.00379 -0.0652 0.6164 1.0000
3.000 0.6194 0.01055 0.00387 -0.0627 0.5462 1.0000
3.250 0.6311 0.01119 0.00405 -0.0594 0.4572 1.0000
3.500 0.6417 0.01192 0.00433 -0.0561 0.3680 1.0000
3.750 0.6552 0.01257 0.00463 -0.0535 0.3037 1.0000
4.000 0.6709 0.01312 0.00493 -0.0512 0.2566 1.0000
4.250 0.6877 0.01363 0.00523 -0.0492 0.2183 1.0000
4.500 0.7054 0.01411 0.00554 -0.0474 0.1856 1.0000
4.750 0.7239 0.01458 0.00585 -0.0457 0.1560 1.0000
5.250 0.7628 0.01548 0.00650 -0.0427 0.1130 1.0000
5.500 0.7828 0.01593 0.00688 -0.0413 0.1005 1.0000
6.000 0.8237 0.01682 0.00770 -0.0386 0.0833 1.0000
6.250 0.8440 0.01730 0.00817 -0.0373 0.0764 1.0000
6.500 0.8647 0.01777 0.00863 -0.0361 0.0697 1.0000
6.750 0.8853 0.01826 0.00913 -0.0349 0.0640 1.0000
7.000 0.9053 0.01879 0.00964 -0.0336 0.0591 1.0000
7.250 0.9254 0.01933 0.01022 -0.0323 0.0550 1.0000
7.500 0.9452 0.01989 0.01078 -0.0310 0.0514 1.0000
7.750 0.9645 0.02050 0.01140 -0.0296 0.0485 1.0000
8.000 0.9841 0.02108 0.01203 -0.0283 0.0458 1.0000
8.250 1.0026 0.02173 0.01269 -0.0269 0.0439 1.0000
8.500 1.0205 0.02247 0.01346 -0.0254 0.0423 1.0000
8.750 1.0386 0.02317 0.01424 -0.0239 0.0407 1.0000
9.000 1.0560 0.02387 0.01498 -0.0223 0.0392 1.0000
9.250 1.0726 0.02459 0.01573 -0.0206 0.0380 1.0000
9.500 1.0881 0.02547 0.01662 -0.0189 0.0369 1.0000
9.750 1.1049 0.02633 0.01760 -0.0173 0.0358 1.0000
10.000 1.1211 0.02724 0.01862 -0.0157 0.0349 1.0000
10.250 1.1368 0.02819 0.01964 -0.0141 0.0340 1.0000
10.500 1.1518 0.02913 0.02065 -0.0125 0.0332 1.0000
10.750 1.1660 0.03011 0.02168 -0.0108 0.0325 1.0000
11.000 1.1792 0.03131 0.02289 -0.0091 0.0318 1.0000
11.250 1.1929 0.03246 0.02423 -0.0075 0.0310 1.0000
11.500 1.2055 0.03371 0.02565 -0.0057 0.0303 1.0000
11.750 1.2169 0.03505 0.02714 -0.0040 0.0297 1.0000
12.000 1.2271 0.03645 0.02869 -0.0021 0.0292 1.0000
12.250 1.2361 0.03790 0.03028 -0.0003 0.0287 1.0000
12.500 1.2439 0.03940 0.03189 0.0015 0.0282 1.0000
12.750 1.2509 0.04095 0.03355 0.0032 0.0278 1.0000
13.000 1.2570 0.04260 0.03528 0.0049 0.0275 1.0000
13.250 1.2621 0.04449 0.03725 0.0065 0.0271 1.0000
13.500 1.2611 0.04682 0.03983 0.0083 0.0267 1.0000
13.750 1.2572 0.04946 0.04275 0.0100 0.0264 1.0000
14.000 1.2512 0.05241 0.04596 0.0113 0.0260 1.0000
14.250 1.2432 0.05570 0.04950 0.0123 0.0257 1.0000
14.500 1.2330 0.05941 0.05345 0.0127 0.0255 1.0000
14.750 1.2201 0.06367 0.05794 0.0125 0.0253 1.0000
15.000 1.2040 0.06866 0.06317 0.0115 0.0251 1.0000
15.250 1.1843 0.07458 0.06934 0.0095 0.0250 1.0000
15.500 1.1599 0.08194 0.07695 0.0059 0.0250 1.0000
15.750 1.1264 0.09195 0.08724 0.0000 0.0250 1.0000
16.000 1.0297 0.11926 0.11507 -0.0185 0.0257 1.0000
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Polar data table (+)
Polar graphs
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