LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il) Reynolds number: 500,000 Max Cl/Cd: 65.23 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141e-il-500000-n5.txt Download as CSV file: xf-c141e-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.9689 0.04929 0.04593 -0.0758 1.0000 0.0162
-14.000 -0.9992 0.04268 0.03905 -0.0794 1.0000 0.0162
-13.750 -1.0200 0.03903 0.03520 -0.0784 1.0000 0.0162
-13.500 -1.0395 0.03671 0.03272 -0.0746 1.0000 0.0163
-13.250 -1.0609 0.03521 0.03108 -0.0684 1.0000 0.0164
-13.000 -1.0725 0.03361 0.02931 -0.0635 1.0000 0.0165
-12.750 -1.0780 0.03205 0.02757 -0.0593 1.0000 0.0166
-12.500 -1.0714 0.03036 0.02565 -0.0574 0.9992 0.0168
-12.250 -1.0534 0.02871 0.02382 -0.0574 0.9974 0.0171
-12.000 -1.0320 0.02755 0.02257 -0.0577 0.9959 0.0174
-11.750 -1.0084 0.02662 0.02155 -0.0581 0.9947 0.0177
-11.500 -0.9854 0.02576 0.02061 -0.0582 0.9933 0.0180
-11.250 -0.9630 0.02487 0.01959 -0.0581 0.9914 0.0184
-11.000 -0.9395 0.02391 0.01850 -0.0582 0.9895 0.0188
-10.750 -0.9150 0.02291 0.01735 -0.0584 0.9879 0.0192
-10.500 -0.8896 0.02195 0.01622 -0.0587 0.9865 0.0197
-10.250 -0.8631 0.02108 0.01517 -0.0591 0.9854 0.0201
-10.000 -0.8362 0.02018 0.01419 -0.0597 0.9844 0.0205
-9.750 -0.8106 0.01953 0.01349 -0.0598 0.9827 0.0209
-9.500 -0.7864 0.01898 0.01287 -0.0595 0.9802 0.0213
-9.250 -0.7598 0.01844 0.01227 -0.0597 0.9783 0.0219
-9.000 -0.7317 0.01790 0.01164 -0.0602 0.9767 0.0226
-8.750 -0.7026 0.01734 0.01098 -0.0608 0.9754 0.0233
-8.500 -0.6727 0.01679 0.01032 -0.0616 0.9742 0.0238
-8.250 -0.6430 0.01614 0.00966 -0.0624 0.9733 0.0245
-8.000 -0.6119 0.01567 0.00915 -0.0634 0.9725 0.0251
-7.750 -0.5857 0.01526 0.00870 -0.0633 0.9701 0.0258
-7.500 -0.5608 0.01488 0.00827 -0.0628 0.9668 0.0266
-7.250 -0.5325 0.01449 0.00782 -0.0631 0.9646 0.0275
-7.000 -0.5036 0.01404 0.00733 -0.0635 0.9628 0.0283
-6.750 -0.4739 0.01363 0.00692 -0.0641 0.9612 0.0293
-6.500 -0.4436 0.01327 0.00654 -0.0648 0.9598 0.0302
-6.250 -0.4130 0.01293 0.00617 -0.0655 0.9585 0.0314
-6.000 -0.3904 0.01268 0.00587 -0.0644 0.9540 0.0324
-5.750 -0.3640 0.01232 0.00553 -0.0642 0.9508 0.0338
-5.500 -0.3355 0.01202 0.00523 -0.0644 0.9483 0.0351
-5.250 -0.3061 0.01173 0.00492 -0.0647 0.9462 0.0367
-5.000 -0.2764 0.01144 0.00461 -0.0652 0.9444 0.0385
-4.750 -0.2519 0.01120 0.00440 -0.0645 0.9402 0.0406
-4.500 -0.2255 0.01099 0.00417 -0.0641 0.9361 0.0430
-4.250 -0.1975 0.01073 0.00393 -0.0642 0.9330 0.0455
-4.000 -0.1685 0.01050 0.00371 -0.0644 0.9304 0.0488
-3.750 -0.1406 0.01029 0.00351 -0.0643 0.9272 0.0524
-3.500 -0.1153 0.01012 0.00337 -0.0638 0.9220 0.0567
-3.250 -0.0876 0.00993 0.00319 -0.0637 0.9179 0.0612
-3.000 -0.0587 0.00973 0.00302 -0.0638 0.9147 0.0664
-2.750 -0.0317 0.00957 0.00288 -0.0636 0.9101 0.0721
-2.500 -0.0050 0.00943 0.00276 -0.0633 0.9046 0.0784
-2.250 0.0233 0.00925 0.00262 -0.0633 0.9003 0.0859
-2.000 0.0515 0.00910 0.00249 -0.0633 0.8959 0.0941
-1.750 0.0781 0.00895 0.00240 -0.0630 0.8897 0.1053
-1.500 0.1063 0.00877 0.00228 -0.0630 0.8846 0.1208
-1.250 0.1337 0.00858 0.00218 -0.0628 0.8791 0.1448
-1.000 0.1600 0.00827 0.00207 -0.0625 0.8712 0.2034
-0.750 0.1845 0.00766 0.00193 -0.0621 0.8619 0.3482
-0.500 0.2077 0.00696 0.00180 -0.0613 0.8512 0.5310
-0.250 0.2304 0.00653 0.00179 -0.0601 0.8394 0.6589
0.000 0.2540 0.00626 0.00180 -0.0589 0.8264 0.7461
0.250 0.2778 0.00610 0.00181 -0.0576 0.8077 0.8081
0.500 0.3023 0.00607 0.00183 -0.0564 0.7864 0.8501
0.750 0.3275 0.00611 0.00186 -0.0554 0.7642 0.8808
1.000 0.3524 0.00621 0.00189 -0.0543 0.7367 0.9076
1.250 0.3780 0.00640 0.00197 -0.0534 0.6998 0.9314
1.500 0.4052 0.00665 0.00206 -0.0530 0.6593 0.9513
1.750 0.4340 0.00693 0.00216 -0.0530 0.6169 0.9626
2.000 0.4583 0.00733 0.00228 -0.0522 0.5541 0.9712
2.250 0.4856 0.00791 0.00246 -0.0524 0.4669 0.9762
2.500 0.5105 0.00855 0.00269 -0.0520 0.3761 0.9827
3.000 0.5710 0.00957 0.00314 -0.0538 0.2508 0.9895
3.250 0.6006 0.01000 0.00335 -0.0545 0.2088 0.9934
3.500 0.6321 0.01038 0.00354 -0.0555 0.1749 0.9961
3.750 0.6633 0.01074 0.00375 -0.0566 0.1429 0.9989
4.250 0.7071 0.01135 0.00411 -0.0544 0.1018 1.0000
4.500 0.7270 0.01161 0.00432 -0.0528 0.0914 1.0000
4.750 0.7477 0.01184 0.00451 -0.0514 0.0840 1.0000
5.000 0.7682 0.01210 0.00473 -0.0500 0.0773 1.0000
5.250 0.7893 0.01233 0.00495 -0.0486 0.0716 1.0000
5.500 0.8104 0.01260 0.00518 -0.0473 0.0664 1.0000
5.750 0.8320 0.01285 0.00542 -0.0461 0.0609 1.0000
6.000 0.8538 0.01314 0.00568 -0.0449 0.0555 1.0000
6.250 0.8755 0.01345 0.00595 -0.0438 0.0497 1.0000
6.500 0.8975 0.01376 0.00624 -0.0427 0.0447 1.0000
6.750 0.9196 0.01410 0.00656 -0.0417 0.0410 1.0000
7.000 0.9415 0.01446 0.00690 -0.0406 0.0379 1.0000
7.250 0.9634 0.01482 0.00727 -0.0396 0.0357 1.0000
7.500 0.9854 0.01519 0.00764 -0.0386 0.0338 1.0000
7.750 1.0066 0.01562 0.00806 -0.0375 0.0321 1.0000
8.000 1.0282 0.01602 0.00849 -0.0364 0.0309 1.0000
8.250 1.0496 0.01642 0.00893 -0.0354 0.0299 1.0000
8.500 1.0706 0.01686 0.00939 -0.0343 0.0290 1.0000
8.750 1.0911 0.01733 0.00988 -0.0331 0.0281 1.0000
9.000 1.1103 0.01790 0.01046 -0.0317 0.0272 1.0000
9.250 1.1301 0.01838 0.01099 -0.0304 0.0265 1.0000
9.500 1.1491 0.01885 0.01152 -0.0290 0.0259 1.0000
9.750 1.1672 0.01936 0.01208 -0.0275 0.0252 1.0000
10.000 1.1849 0.01991 0.01267 -0.0259 0.0246 1.0000
10.250 1.2020 0.02049 0.01330 -0.0243 0.0241 1.0000
10.500 1.2184 0.02113 0.01397 -0.0226 0.0236 1.0000
10.750 1.2332 0.02188 0.01476 -0.0207 0.0232 1.0000
11.000 1.2474 0.02268 0.01561 -0.0188 0.0227 1.0000
11.250 1.2635 0.02334 0.01636 -0.0172 0.0223 1.0000
11.500 1.2789 0.02404 0.01715 -0.0156 0.0219 1.0000
11.750 1.2936 0.02480 0.01798 -0.0139 0.0214 1.0000
12.000 1.3077 0.02560 0.01885 -0.0122 0.0210 1.0000
12.250 1.3208 0.02646 0.01978 -0.0105 0.0207 1.0000
12.500 1.3333 0.02737 0.02077 -0.0088 0.0203 1.0000
12.750 1.3448 0.02835 0.02181 -0.0070 0.0200 1.0000
13.000 1.3551 0.02943 0.02297 -0.0052 0.0197 1.0000
13.250 1.3633 0.03069 0.02429 -0.0033 0.0195 1.0000
13.500 1.3688 0.03221 0.02588 -0.0013 0.0192 1.0000
13.750 1.3775 0.03350 0.02730 0.0003 0.0190 1.0000
14.000 1.3850 0.03491 0.02883 0.0018 0.0188 1.0000
14.250 1.3915 0.03645 0.03050 0.0033 0.0186 1.0000
14.500 1.3970 0.03812 0.03229 0.0047 0.0183 1.0000
14.750 1.4014 0.03992 0.03422 0.0060 0.0181 1.0000
15.000 1.4048 0.04189 0.03631 0.0071 0.0178 1.0000
15.250 1.4072 0.04401 0.03856 0.0080 0.0176 1.0000
15.500 1.4084 0.04635 0.04101 0.0087 0.0174 1.0000
15.750 1.4082 0.04893 0.04371 0.0092 0.0172 1.0000
16.000 1.4068 0.05177 0.04668 0.0094 0.0170 1.0000
16.250 1.4036 0.05497 0.04999 0.0092 0.0169 1.0000
16.500 1.3990 0.05853 0.05368 0.0087 0.0168 1.0000
16.750 1.3928 0.06252 0.05780 0.0077 0.0166 1.0000
17.000 1.3845 0.06703 0.06245 0.0063 0.0165 1.0000
17.250 1.3742 0.07209 0.06765 0.0043 0.0165 1.0000
17.500 1.3615 0.07782 0.07352 0.0017 0.0164 1.0000
17.750 1.3462 0.08427 0.08012 -0.0014 0.0163 1.0000
18.000 1.3281 0.09147 0.08747 -0.0052 0.0163 1.0000
18.250 1.3076 0.09939 0.09556 -0.0094 0.0162 1.0000
18.500 1.2848 0.10797 0.10429 -0.0142 0.0162 1.0000
18.750 1.2593 0.11719 0.11367 -0.0193 0.0162 1.0000
19.000 1.2329 0.12684 0.12348 -0.0248 0.0162 1.0000
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Polar data table (+)
Polar graphs
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