LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Reynolds number: 500,000 Max Cl/Cd: 70.05 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141f-il-500000-n5.txt Download as CSV file: xf-c141f-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL958.89 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4897 0.09881 0.09617 -0.0326 1.0000 0.0185
-10.000 -0.4910 0.09528 0.09266 -0.0338 0.9996 0.0188
-9.500 -0.6984 0.02733 0.02278 -0.0761 0.9787 0.0227
-9.250 -0.6843 0.02320 0.01796 -0.0760 0.9765 0.0234
-9.000 -0.6595 0.02164 0.01614 -0.0764 0.9754 0.0238
-8.750 -0.6310 0.02094 0.01538 -0.0771 0.9745 0.0241
-8.500 -0.6013 0.02033 0.01472 -0.0779 0.9737 0.0243
-8.250 -0.5713 0.01972 0.01403 -0.0788 0.9731 0.0247
-8.000 -0.5463 0.01914 0.01336 -0.0785 0.9711 0.0251
-7.750 -0.5235 0.01850 0.01261 -0.0777 0.9682 0.0256
-7.500 -0.4969 0.01771 0.01165 -0.0778 0.9662 0.0262
-7.250 -0.4691 0.01689 0.01066 -0.0780 0.9646 0.0268
-7.000 -0.4402 0.01620 0.00986 -0.0784 0.9632 0.0272
-6.750 -0.4104 0.01572 0.00937 -0.0791 0.9620 0.0276
-6.500 -0.3800 0.01530 0.00893 -0.0797 0.9609 0.0280
-6.250 -0.3494 0.01487 0.00846 -0.0804 0.9598 0.0285
-6.000 -0.3245 0.01450 0.00803 -0.0798 0.9570 0.0291
-5.750 -0.2996 0.01411 0.00758 -0.0792 0.9536 0.0298
-5.500 -0.2718 0.01370 0.00709 -0.0791 0.9512 0.0305
-5.250 -0.2433 0.01326 0.00664 -0.0793 0.9491 0.0311
-5.000 -0.2138 0.01292 0.00630 -0.0797 0.9473 0.0317
-4.750 -0.1838 0.01259 0.00597 -0.0801 0.9456 0.0324
-4.500 -0.1561 0.01228 0.00564 -0.0800 0.9432 0.0332
-4.250 -0.1322 0.01201 0.00535 -0.0791 0.9388 0.0340
-4.000 -0.1052 0.01171 0.00503 -0.0788 0.9355 0.0349
-3.750 -0.0768 0.01141 0.00476 -0.0788 0.9328 0.0359
-3.500 -0.0475 0.01114 0.00449 -0.0790 0.9304 0.0369
-3.250 -0.0192 0.01088 0.00423 -0.0790 0.9278 0.0380
-3.000 0.0050 0.01068 0.00402 -0.0781 0.9222 0.0389
-2.750 0.0323 0.01038 0.00375 -0.0778 0.9171 0.0402
-2.500 0.0615 0.01011 0.00349 -0.0779 0.9127 0.0417
-2.250 0.0862 0.00994 0.00333 -0.0770 0.9049 0.0433
-2.000 0.1137 0.00970 0.00310 -0.0768 0.8986 0.0448
-1.750 0.1401 0.00949 0.00293 -0.0763 0.8899 0.0466
-1.500 0.1681 0.00930 0.00273 -0.0761 0.8820 0.0488
-1.250 0.1953 0.00911 0.00258 -0.0758 0.8723 0.0515
-1.000 0.2239 0.00893 0.00239 -0.0756 0.8611 0.0547
-0.750 0.2526 0.00876 0.00221 -0.0755 0.8468 0.0588
-0.500 0.2809 0.00864 0.00206 -0.0754 0.8311 0.0650
-0.250 0.3087 0.00857 0.00197 -0.0751 0.8150 0.0735
0.000 0.3356 0.00853 0.00191 -0.0747 0.7945 0.0849
0.250 0.3616 0.00853 0.00185 -0.0741 0.7651 0.0989
0.500 0.3862 0.00859 0.00181 -0.0731 0.7266 0.1174
0.750 0.4096 0.00866 0.00180 -0.0721 0.6808 0.1555
1.000 0.4247 0.00741 0.00185 -0.0702 0.6362 0.6523
1.250 0.4428 0.00742 0.00197 -0.0679 0.5760 0.7608
1.500 0.4583 0.00767 0.00218 -0.0650 0.4985 0.8535
1.750 0.4755 0.00818 0.00243 -0.0624 0.4061 0.9213
2.000 0.5065 0.00891 0.00274 -0.0632 0.3044 0.9722
2.250 0.5448 0.00936 0.00293 -0.0657 0.2554 0.9898
2.500 0.5844 0.00970 0.00310 -0.0684 0.2267 0.9987
3.000 0.6322 0.01010 0.00332 -0.0668 0.1989 1.0000
3.250 0.6549 0.01029 0.00345 -0.0657 0.1886 1.0000
3.500 0.6778 0.01048 0.00358 -0.0646 0.1778 1.0000
3.750 0.7013 0.01067 0.00371 -0.0637 0.1672 1.0000
4.000 0.7247 0.01089 0.00387 -0.0627 0.1544 1.0000
4.250 0.7480 0.01115 0.00403 -0.0618 0.1375 1.0000
4.500 0.7708 0.01147 0.00422 -0.0608 0.1173 1.0000
4.750 0.7939 0.01179 0.00444 -0.0599 0.1034 1.0000
5.000 0.8173 0.01209 0.00468 -0.0590 0.0951 1.0000
5.250 0.8413 0.01235 0.00491 -0.0582 0.0904 1.0000
5.500 0.8649 0.01265 0.00517 -0.0574 0.0863 1.0000
5.750 0.8889 0.01293 0.00544 -0.0566 0.0831 1.0000
6.000 0.9127 0.01321 0.00571 -0.0559 0.0796 1.0000
6.250 0.9359 0.01355 0.00601 -0.0550 0.0760 1.0000
6.500 0.9599 0.01382 0.00629 -0.0543 0.0734 1.0000
6.750 0.9836 0.01411 0.00658 -0.0535 0.0709 1.0000
7.000 1.0067 0.01444 0.00689 -0.0527 0.0682 1.0000
7.250 1.0299 0.01477 0.00722 -0.0519 0.0660 1.0000
7.500 1.0535 0.01504 0.00753 -0.0511 0.0637 1.0000
7.750 1.0766 0.01537 0.00784 -0.0503 0.0613 1.0000
8.000 1.0990 0.01573 0.00821 -0.0494 0.0590 1.0000
8.250 1.1222 0.01602 0.00853 -0.0486 0.0568 1.0000
8.500 1.1449 0.01635 0.00887 -0.0477 0.0543 1.0000
8.750 1.1671 0.01670 0.00923 -0.0468 0.0518 1.0000
9.000 1.1894 0.01702 0.00958 -0.0459 0.0485 1.0000
9.250 1.2111 0.01739 0.00995 -0.0449 0.0450 1.0000
9.500 1.2321 0.01778 0.01034 -0.0438 0.0408 1.0000
9.750 1.2517 0.01822 0.01076 -0.0424 0.0366 1.0000
10.000 1.2705 0.01872 0.01125 -0.0410 0.0330 1.0000
10.250 1.2888 0.01925 0.01180 -0.0395 0.0303 1.0000
10.500 1.3065 0.01983 0.01240 -0.0379 0.0282 1.0000
10.750 1.3240 0.02042 0.01302 -0.0363 0.0264 1.0000
11.000 1.3406 0.02109 0.01371 -0.0347 0.0250 1.0000
11.250 1.3576 0.02170 0.01438 -0.0331 0.0239 1.0000
11.500 1.3736 0.02238 0.01511 -0.0314 0.0228 1.0000
12.000 1.4038 0.02385 0.01669 -0.0280 0.0211 1.0000
12.250 1.4184 0.02461 0.01751 -0.0263 0.0204 1.0000
12.500 1.4321 0.02543 0.01840 -0.0245 0.0197 1.0000
12.750 1.4444 0.02636 0.01938 -0.0226 0.0192 1.0000
13.000 1.4553 0.02738 0.02046 -0.0206 0.0187 1.0000
13.250 1.4671 0.02833 0.02150 -0.0188 0.0184 1.0000
13.500 1.4778 0.02936 0.02263 -0.0170 0.0180 1.0000
13.750 1.4876 0.03048 0.02384 -0.0151 0.0176 1.0000
14.000 1.4964 0.03170 0.02514 -0.0133 0.0173 1.0000
14.250 1.5040 0.03302 0.02656 -0.0115 0.0170 1.0000
14.500 1.5102 0.03449 0.02811 -0.0098 0.0167 1.0000
14.750 1.5149 0.03614 0.02985 -0.0081 0.0164 1.0000
15.000 1.5175 0.03801 0.03182 -0.0064 0.0162 1.0000
15.250 1.5177 0.04019 0.03409 -0.0049 0.0160 1.0000
15.500 1.5198 0.04229 0.03631 -0.0038 0.0159 1.0000
15.750 1.5203 0.04462 0.03877 -0.0028 0.0157 1.0000
16.000 1.5191 0.04724 0.04152 -0.0020 0.0156 1.0000
16.250 1.5165 0.05018 0.04459 -0.0016 0.0154 1.0000
16.500 1.5118 0.05349 0.04804 -0.0015 0.0153 1.0000
16.750 1.5054 0.05727 0.05195 -0.0018 0.0152 1.0000
17.000 1.4971 0.06153 0.05636 -0.0027 0.0151 1.0000
17.250 1.4863 0.06645 0.06143 -0.0042 0.0149 1.0000
17.500 1.4722 0.07215 0.06729 -0.0064 0.0149 1.0000
17.750 1.4547 0.07883 0.07414 -0.0094 0.0148 1.0000
18.000 1.4330 0.08664 0.08213 -0.0133 0.0148 1.0000
18.250 1.4066 0.09565 0.09133 -0.0180 0.0148 1.0000
18.500 1.3771 0.10548 0.10134 -0.0232 0.0148 1.0000
18.750 1.3462 0.11553 0.11157 -0.0285 0.0148 1.0000
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