LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Reynolds number: 200,000 Max Cl/Cd: 66.89 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141c-il-200000.txt Download as CSV file: xf-c141c-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL426.57 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5373 0.10149 0.09765 -0.0432 1.0000 0.0686
-10.500 -0.5661 0.09272 0.08893 -0.0525 1.0000 0.0689
-10.250 -0.5940 0.08766 0.08385 -0.0554 1.0000 0.0690
-10.000 -0.5638 0.08467 0.08097 -0.0498 1.0000 0.0706
-9.750 -0.5579 0.08285 0.07916 -0.0475 1.0000 0.0715
-9.500 -0.5745 0.07810 0.07445 -0.0496 1.0000 0.0721
-9.250 -0.6037 0.07439 0.07076 -0.0486 1.0000 0.0723
-9.000 -0.6326 0.07186 0.06823 -0.0446 1.0000 0.0724
-8.750 -0.6500 0.06919 0.06554 -0.0414 1.0000 0.0731
-8.500 -0.6655 0.06648 0.06279 -0.0383 1.0000 0.0739
-8.250 -0.7615 0.04796 0.04292 -0.0292 1.0000 0.0471
-8.000 -0.7623 0.04400 0.03879 -0.0264 1.0000 0.0460
-7.750 -0.7622 0.04012 0.03459 -0.0232 1.0000 0.0450
-7.500 -0.7589 0.03628 0.03033 -0.0201 1.0000 0.0444
-7.250 -0.7504 0.03311 0.02672 -0.0175 1.0000 0.0445
-7.000 -0.7374 0.03085 0.02405 -0.0153 1.0000 0.0457
-6.750 -0.7217 0.02896 0.02175 -0.0133 1.0000 0.0468
-6.500 -0.7038 0.02748 0.01986 -0.0115 1.0000 0.0476
-6.250 -0.6834 0.02477 0.01694 -0.0107 1.0000 0.0491
-6.000 -0.6623 0.02367 0.01578 -0.0098 1.0000 0.0509
-5.750 -0.6411 0.02293 0.01494 -0.0088 1.0000 0.0536
-5.500 -0.6194 0.02225 0.01406 -0.0077 1.0000 0.0566
-5.250 -0.5968 0.02090 0.01259 -0.0070 1.0000 0.0594
-5.000 -0.5750 0.02020 0.01192 -0.0061 1.0000 0.0628
-4.750 -0.5459 0.01977 0.01138 -0.0067 0.9986 0.0679
-4.500 -0.5123 0.01881 0.01045 -0.0082 0.9962 0.0735
-4.250 -0.4764 0.01850 0.01007 -0.0101 0.9936 0.0810
-4.000 -0.4448 0.01775 0.00942 -0.0113 0.9904 0.0893
-3.750 -0.4109 0.01724 0.00894 -0.0129 0.9872 0.1008
-3.500 -0.3749 0.01680 0.00857 -0.0150 0.9845 0.1168
-3.250 -0.3429 0.01633 0.00823 -0.0162 0.9809 0.1420
-3.000 -0.3116 0.01567 0.00790 -0.0175 0.9768 0.1967
-2.750 -0.2810 0.01432 0.00766 -0.0193 0.9741 0.4176
-2.500 -0.2512 0.01343 0.00789 -0.0197 0.9718 0.6726
-2.250 -0.2257 0.01331 0.00807 -0.0187 0.9669 0.7668
-2.000 -0.1981 0.01335 0.00827 -0.0180 0.9620 0.8276
-1.750 -0.1656 0.01356 0.00854 -0.0181 0.9585 0.8759
-1.500 -0.1343 0.01383 0.00880 -0.0182 0.9544 0.9118
-1.250 -0.1012 0.01408 0.00901 -0.0188 0.9493 0.9410
-1.000 -0.0509 0.01440 0.00926 -0.0231 0.9474 0.9602
-0.750 0.0083 0.01472 0.00950 -0.0294 0.9469 0.9739
-0.500 0.0899 0.01510 0.00982 -0.0403 0.9503 0.9887
-0.250 0.1548 0.01516 0.00985 -0.0482 0.9504 0.9971
0.000 0.2018 0.01509 0.00975 -0.0527 0.9469 1.0000
0.250 0.2444 0.01496 0.00961 -0.0562 0.9434 1.0000
0.500 0.2694 0.01487 0.00952 -0.0563 0.9346 1.0000
0.750 0.3116 0.01471 0.00936 -0.0595 0.9302 1.0000
1.000 0.3675 0.01436 0.00904 -0.0652 0.9276 1.0000
1.250 0.4045 0.01388 0.00859 -0.0667 0.9165 1.0000
1.500 0.4507 0.01305 0.00779 -0.0694 0.9048 1.0000
1.750 0.4884 0.01237 0.00713 -0.0705 0.8946 1.0000
2.000 0.5166 0.01190 0.00669 -0.0700 0.8831 1.0000
2.250 0.5393 0.01157 0.00639 -0.0685 0.8692 1.0000
2.500 0.5625 0.01124 0.00609 -0.0670 0.8543 1.0000
2.750 0.5859 0.01092 0.00579 -0.0656 0.8377 1.0000
3.000 0.6079 0.01067 0.00556 -0.0639 0.8175 1.0000
3.250 0.6303 0.01046 0.00534 -0.0622 0.7927 1.0000
3.500 0.6530 0.01029 0.00514 -0.0606 0.7613 1.0000
3.750 0.6749 0.01025 0.00499 -0.0588 0.7189 1.0000
4.000 0.6950 0.01039 0.00490 -0.0567 0.6569 1.0000
4.250 0.7091 0.01085 0.00492 -0.0536 0.5647 1.0000
4.500 0.7139 0.01177 0.00517 -0.0489 0.4371 1.0000
4.750 0.7160 0.01292 0.00563 -0.0442 0.3137 1.0000
5.000 0.7227 0.01395 0.00614 -0.0405 0.2259 1.0000
5.250 0.7334 0.01481 0.00668 -0.0375 0.1758 1.0000
5.500 0.7462 0.01557 0.00722 -0.0348 0.1454 1.0000
5.750 0.7608 0.01624 0.00778 -0.0323 0.1245 1.0000
6.000 0.7758 0.01692 0.00838 -0.0300 0.1095 1.0000
6.250 0.7913 0.01765 0.00904 -0.0278 0.0979 1.0000
6.500 0.8070 0.01846 0.00976 -0.0257 0.0883 1.0000
6.750 0.8261 0.01904 0.01039 -0.0240 0.0805 1.0000
7.000 0.8433 0.02003 0.01131 -0.0223 0.0739 1.0000
7.250 0.8634 0.02067 0.01202 -0.0209 0.0683 1.0000
7.500 0.8830 0.02194 0.01320 -0.0198 0.0630 1.0000
7.750 0.9042 0.02263 0.01402 -0.0185 0.0591 1.0000
8.000 0.9256 0.02354 0.01495 -0.0175 0.0557 1.0000
8.250 0.9506 0.02543 0.01680 -0.0175 0.0525 1.0000
8.500 0.9716 0.02629 0.01787 -0.0162 0.0500 1.0000
8.750 0.9926 0.02732 0.01902 -0.0152 0.0475 1.0000
9.000 1.0141 0.02856 0.02032 -0.0143 0.0456 1.0000
9.250 1.0379 0.03077 0.02256 -0.0142 0.0440 1.0000
9.500 1.0566 0.03324 0.02535 -0.0130 0.0430 1.0000
9.750 1.0711 0.03504 0.02749 -0.0109 0.0422 1.0000
10.000 1.0831 0.03707 0.02987 -0.0086 0.0411 1.0000
10.250 1.0927 0.03924 0.03235 -0.0062 0.0401 1.0000
10.500 1.0991 0.04180 0.03524 -0.0035 0.0394 1.0000
10.750 1.0998 0.04493 0.03873 -0.0003 0.0392 1.0000
11.000 1.0931 0.04850 0.04268 0.0036 0.0393 1.0000
11.250 1.0775 0.05227 0.04683 0.0082 0.0396 1.0000
11.500 1.0564 0.05617 0.05103 0.0128 0.0401 1.0000
11.750 1.0328 0.06027 0.05541 0.0165 0.0406 1.0000
12.000 1.0081 0.06467 0.06004 0.0190 0.0411 1.0000
12.250 0.9828 0.06948 0.06505 0.0202 0.0416 1.0000
12.500 0.9571 0.07489 0.07062 0.0199 0.0420 1.0000
12.750 0.9318 0.08101 0.07688 0.0182 0.0425 1.0000
13.000 0.9130 0.08745 0.08339 0.0160 0.0431 1.0000
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Polar data table (+)
Polar graphs
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