LOCKHEED C-141 BL113.6 AIRFOIL (c141b-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL113.6 AIRFOIL (c141b-il) Reynolds number: 500,000 Max Cl/Cd: 69.05 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141b-il-500000.txt Download as CSV file: xf-c141b-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL113.6 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.9264 0.07366 0.07016 -0.0672 1.0000 0.0205
-15.750 -0.9529 0.06574 0.06205 -0.0723 1.0000 0.0204
-15.500 -0.9742 0.05934 0.05546 -0.0759 1.0000 0.0204
-15.250 -0.9916 0.05415 0.05006 -0.0784 1.0000 0.0205
-15.000 -1.0075 0.04967 0.04539 -0.0797 1.0000 0.0206
-14.750 -1.0251 0.04531 0.04083 -0.0800 1.0000 0.0207
-14.500 -1.0353 0.04209 0.03747 -0.0794 1.0000 0.0209
-14.250 -1.0398 0.03975 0.03505 -0.0782 1.0000 0.0211
-14.000 -1.0425 0.03792 0.03315 -0.0765 1.0000 0.0213
-13.750 -1.0454 0.03640 0.03155 -0.0742 1.0000 0.0216
-13.500 -1.0496 0.03505 0.03013 -0.0713 1.0000 0.0218
-13.250 -1.0561 0.03390 0.02889 -0.0674 1.0000 0.0220
-13.000 -1.0658 0.03290 0.02780 -0.0625 1.0000 0.0222
-12.750 -1.0787 0.03208 0.02690 -0.0567 1.0000 0.0223
-12.500 -1.0952 0.03144 0.02617 -0.0497 1.0000 0.0225
-12.250 -1.1074 0.03075 0.02539 -0.0434 1.0000 0.0227
-12.000 -1.1107 0.02988 0.02441 -0.0387 1.0000 0.0229
-11.750 -1.1003 0.02877 0.02315 -0.0367 0.9992 0.0233
-11.500 -1.0788 0.02755 0.02175 -0.0367 0.9974 0.0239
-11.250 -1.0551 0.02657 0.02059 -0.0370 0.9957 0.0243
-11.000 -1.0344 0.02482 0.01875 -0.0371 0.9943 0.0251
-10.750 -1.0116 0.02398 0.01787 -0.0371 0.9923 0.0258
-10.500 -0.9875 0.02326 0.01710 -0.0372 0.9900 0.0265
-10.250 -0.9621 0.02258 0.01633 -0.0374 0.9880 0.0275
-10.000 -0.9353 0.02199 0.01561 -0.0378 0.9865 0.0285
-9.750 -0.9106 0.02089 0.01446 -0.0381 0.9851 0.0297
-9.500 -0.8823 0.02031 0.01387 -0.0389 0.9841 0.0309
-9.250 -0.8584 0.01980 0.01331 -0.0387 0.9819 0.0321
-9.000 -0.8357 0.01933 0.01275 -0.0380 0.9789 0.0334
-8.750 -0.8123 0.01850 0.01188 -0.0377 0.9767 0.0349
-8.500 -0.7848 0.01805 0.01143 -0.0382 0.9750 0.0366
-8.250 -0.7551 0.01770 0.01102 -0.0390 0.9738 0.0387
-8.000 -0.7262 0.01706 0.01035 -0.0397 0.9726 0.0409
-7.750 -0.6950 0.01664 0.00995 -0.0409 0.9716 0.0433
-7.500 -0.6762 0.01636 0.00962 -0.0392 0.9679 0.0453
-7.250 -0.6520 0.01585 0.00907 -0.0388 0.9647 0.0477
-7.000 -0.6225 0.01545 0.00869 -0.0395 0.9626 0.0508
-6.750 -0.5906 0.01518 0.00839 -0.0406 0.9611 0.0538
-6.500 -0.5605 0.01464 0.00787 -0.0415 0.9598 0.0579
-6.250 -0.5273 0.01437 0.00759 -0.0429 0.9588 0.0620
-6.000 -0.4948 0.01393 0.00717 -0.0442 0.9580 0.0672
-5.750 -0.4802 0.01377 0.00700 -0.0415 0.9528 0.0713
-5.500 -0.4544 0.01344 0.00668 -0.0413 0.9500 0.0772
-5.250 -0.4236 0.01317 0.00642 -0.0421 0.9481 0.0846
-5.000 -0.3922 0.01280 0.00612 -0.0431 0.9467 0.0957
-4.750 -0.3591 0.01245 0.00584 -0.0445 0.9455 0.1103
-4.500 -0.3257 0.01207 0.00557 -0.0459 0.9445 0.1315
-4.250 -0.2932 0.01169 0.00532 -0.0471 0.9435 0.1613
-4.000 -0.2741 0.01141 0.00520 -0.0455 0.9392 0.1958
-3.750 -0.2527 0.01103 0.00503 -0.0444 0.9350 0.2458
-3.500 -0.2265 0.01044 0.00478 -0.0444 0.9325 0.3274
-3.250 -0.2003 0.00974 0.00453 -0.0444 0.9305 0.4387
-3.000 -0.1730 0.00918 0.00435 -0.0445 0.9288 0.5359
-2.750 -0.1437 0.00883 0.00425 -0.0447 0.9274 0.6038
-2.500 -0.1282 0.00876 0.00430 -0.0421 0.9209 0.6422
-2.250 -0.1010 0.00859 0.00424 -0.0418 0.9177 0.6773
-2.000 -0.0708 0.00844 0.00414 -0.0421 0.9155 0.7059
-1.750 -0.0395 0.00828 0.00404 -0.0426 0.9136 0.7275
-1.500 -0.0077 0.00814 0.00393 -0.0432 0.9119 0.7461
-1.250 0.0134 0.00812 0.00397 -0.0416 0.9060 0.7624
-1.000 0.0413 0.00801 0.00390 -0.0414 0.9022 0.7782
-0.750 0.0715 0.00786 0.00380 -0.0416 0.8994 0.7942
-0.500 0.1028 0.00772 0.00370 -0.0421 0.8970 0.8102
-0.250 0.1287 0.00767 0.00370 -0.0414 0.8923 0.8270
0.000 0.1540 0.00760 0.00371 -0.0405 0.8868 0.8465
0.250 0.1838 0.00747 0.00363 -0.0404 0.8829 0.8629
0.500 0.2117 0.00730 0.00346 -0.0400 0.8755 0.8752
0.750 0.2433 0.00702 0.00318 -0.0401 0.8647 0.8837
1.000 0.2682 0.00691 0.00308 -0.0391 0.8529 0.8943
1.250 0.2973 0.00685 0.00303 -0.0389 0.8441 0.9034
1.500 0.3249 0.00680 0.00299 -0.0385 0.8331 0.9125
1.750 0.3505 0.00680 0.00301 -0.0377 0.8205 0.9227
2.000 0.3796 0.00682 0.00302 -0.0377 0.8062 0.9300
2.250 0.4060 0.00684 0.00302 -0.0370 0.7886 0.9394
2.500 0.4370 0.00691 0.00304 -0.0374 0.7659 0.9449
2.750 0.4661 0.00704 0.00307 -0.0374 0.7340 0.9516
3.000 0.4935 0.00727 0.00313 -0.0371 0.6951 0.9582
3.250 0.5248 0.00760 0.00328 -0.0377 0.6481 0.9624
3.500 0.5483 0.00801 0.00345 -0.0368 0.5910 0.9705
3.750 0.5791 0.00868 0.00370 -0.0377 0.4981 0.9734
4.000 0.6052 0.00960 0.00407 -0.0380 0.3806 0.9784
4.250 0.6309 0.01046 0.00445 -0.0382 0.2819 0.9841
4.500 0.6638 0.01117 0.00479 -0.0399 0.2119 0.9870
4.750 0.6968 0.01171 0.00511 -0.0415 0.1671 0.9907
5.000 0.7297 0.01220 0.00542 -0.0430 0.1362 0.9942
5.250 0.7650 0.01262 0.00573 -0.0451 0.1133 0.9967
5.500 0.7999 0.01303 0.00604 -0.0470 0.0970 0.9993
5.750 0.8196 0.01335 0.00631 -0.0457 0.0871 1.0000
6.000 0.8317 0.01368 0.00657 -0.0428 0.0794 1.0000
6.250 0.8457 0.01390 0.00681 -0.0401 0.0741 1.0000
6.500 0.8572 0.01427 0.00713 -0.0370 0.0684 1.0000
6.750 0.8712 0.01450 0.00738 -0.0343 0.0644 1.0000
7.000 0.8839 0.01482 0.00767 -0.0315 0.0604 1.0000
7.250 0.8957 0.01520 0.00806 -0.0284 0.0569 1.0000
7.500 0.9099 0.01547 0.00836 -0.0258 0.0540 1.0000
7.750 0.9218 0.01588 0.00873 -0.0228 0.0511 1.0000
8.000 0.9319 0.01630 0.00918 -0.0194 0.0488 1.0000
8.250 0.9455 0.01660 0.00951 -0.0167 0.0465 1.0000
8.500 0.9595 0.01699 0.00989 -0.0142 0.0442 1.0000
8.750 0.9715 0.01763 0.01053 -0.0115 0.0421 1.0000
9.000 0.9889 0.01802 0.01098 -0.0097 0.0403 1.0000
9.250 1.0058 0.01848 0.01147 -0.0079 0.0385 1.0000
9.500 1.0201 0.01917 0.01214 -0.0059 0.0369 1.0000
9.750 1.0350 0.01989 0.01292 -0.0039 0.0355 1.0000
10.000 1.0525 0.02042 0.01351 -0.0024 0.0341 1.0000
10.250 1.0695 0.02098 0.01410 -0.0009 0.0328 1.0000
10.500 1.0846 0.02169 0.01481 0.0008 0.0316 1.0000
10.750 1.0971 0.02273 0.01589 0.0028 0.0305 1.0000
11.000 1.1135 0.02340 0.01665 0.0044 0.0296 1.0000
11.250 1.1288 0.02416 0.01749 0.0059 0.0287 1.0000
11.500 1.1435 0.02494 0.01832 0.0075 0.0279 1.0000
11.750 1.1573 0.02579 0.01920 0.0091 0.0272 1.0000
12.000 1.1693 0.02688 0.02032 0.0108 0.0265 1.0000
12.250 1.1794 0.02839 0.02190 0.0127 0.0259 1.0000
12.500 1.1920 0.02937 0.02301 0.0143 0.0255 1.0000
12.750 1.2036 0.03046 0.02421 0.0160 0.0250 1.0000
13.000 1.2141 0.03160 0.02546 0.0176 0.0244 1.0000
13.250 1.2240 0.03279 0.02675 0.0192 0.0239 1.0000
13.500 1.2330 0.03403 0.02807 0.0207 0.0234 1.0000
13.750 1.2412 0.03535 0.02946 0.0222 0.0230 1.0000
14.000 1.2484 0.03684 0.03100 0.0237 0.0227 1.0000
14.250 1.2537 0.03860 0.03284 0.0252 0.0223 1.0000
14.500 1.2543 0.04114 0.03549 0.0269 0.0220 1.0000
14.750 1.2547 0.04335 0.03788 0.0283 0.0218 1.0000
15.000 1.2544 0.04560 0.04029 0.0296 0.0216 1.0000
15.250 1.2521 0.04814 0.04301 0.0306 0.0214 1.0000
15.500 1.2479 0.05102 0.04606 0.0313 0.0212 1.0000
15.750 1.2414 0.05426 0.04950 0.0317 0.0211 1.0000
16.000 1.2330 0.05791 0.05333 0.0317 0.0209 1.0000
16.250 1.2225 0.06208 0.05768 0.0311 0.0208 1.0000
16.500 1.2096 0.06680 0.06259 0.0300 0.0207 1.0000
16.750 1.1939 0.07227 0.06825 0.0281 0.0206 1.0000
17.000 1.1751 0.07865 0.07483 0.0253 0.0205 1.0000
17.250 1.1516 0.08625 0.08264 0.0214 0.0205 1.0000
17.500 1.1220 0.09561 0.09223 0.0160 0.0206 1.0000
17.750 1.0817 0.10797 0.10483 0.0084 0.0207 1.0000
18.000 0.9621 0.14057 0.13789 -0.0118 0.0215 1.0000
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Polar data table (+)
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