LOCKHEED C-141 BL0 AIRFOIL (c141a-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL0 AIRFOIL (c141a-il) Reynolds number: 50,000 Max Cl/Cd: 27.76 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141a-il-50000-n5.txt Download as CSV file: xf-c141a-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL0 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6836 0.07965 0.07140 -0.0633 1.0000 0.0683
-11.250 -0.7130 0.07508 0.06676 -0.0629 1.0000 0.0681
-11.000 -0.7426 0.07148 0.06308 -0.0605 1.0000 0.0680
-10.750 -0.7724 0.06867 0.06020 -0.0561 1.0000 0.0679
-10.500 -0.7995 0.06579 0.05717 -0.0514 1.0000 0.0680
-10.250 -0.8232 0.06272 0.05385 -0.0467 1.0000 0.0683
-10.000 -0.8317 0.06018 0.05121 -0.0432 1.0000 0.0690
-9.750 -0.8350 0.05796 0.04887 -0.0400 1.0000 0.0699
-9.500 -0.8351 0.05599 0.04680 -0.0370 1.0000 0.0713
-9.250 -0.8370 0.05382 0.04444 -0.0338 1.0000 0.0730
-9.000 -0.8393 0.05139 0.04171 -0.0303 1.0000 0.0749
-8.750 -0.8404 0.04874 0.03864 -0.0269 1.0000 0.0769
-8.500 -0.8389 0.04602 0.03538 -0.0235 1.0000 0.0788
-8.250 -0.8269 0.04434 0.03370 -0.0216 1.0000 0.0811
-8.000 -0.8150 0.04282 0.03203 -0.0196 1.0000 0.0842
-7.750 -0.8029 0.04099 0.02989 -0.0174 1.0000 0.0877
-7.500 -0.7890 0.03909 0.02756 -0.0153 1.0000 0.0912
-7.250 -0.7724 0.03782 0.02634 -0.0139 1.0000 0.0949
-7.000 -0.7552 0.03649 0.02481 -0.0123 1.0000 0.0996
-6.750 -0.7364 0.03510 0.02314 -0.0109 1.0000 0.1046
-6.500 -0.7177 0.03404 0.02213 -0.0096 1.0000 0.1100
-6.250 -0.6973 0.03296 0.02082 -0.0083 1.0000 0.1167
-6.000 -0.6774 0.03197 0.01988 -0.0071 1.0000 0.1234
-5.750 -0.6565 0.03110 0.01883 -0.0059 1.0000 0.1320
-5.500 -0.6370 0.03023 0.01805 -0.0046 1.0000 0.1409
-5.250 -0.6171 0.02942 0.01719 -0.0034 1.0000 0.1520
-5.000 -0.5977 0.02866 0.01641 -0.0020 1.0000 0.1655
-4.750 -0.5789 0.02787 0.01568 -0.0007 1.0000 0.1819
-4.500 -0.5606 0.02706 0.01499 0.0006 1.0000 0.2033
-4.250 -0.5425 0.02622 0.01430 0.0019 1.0000 0.2331
-4.000 -0.5250 0.02527 0.01367 0.0031 1.0000 0.2802
-3.750 -0.5104 0.02417 0.01316 0.0050 1.0000 0.3625
-3.500 -0.4976 0.02325 0.01311 0.0079 1.0000 0.5000
-3.250 -0.4822 0.02304 0.01341 0.0114 1.0000 0.6218
-3.000 -0.4654 0.02312 0.01362 0.0144 1.0000 0.6999
-2.750 -0.4474 0.02329 0.01381 0.0172 1.0000 0.7559
-2.500 -0.4256 0.02359 0.01411 0.0195 1.0000 0.8021
-2.250 -0.3992 0.02402 0.01449 0.0208 1.0000 0.8439
-2.000 -0.3642 0.02461 0.01498 0.0204 1.0000 0.8827
-1.750 -0.3140 0.02548 0.01568 0.0170 1.0000 0.9216
-1.500 -0.2410 0.02649 0.01646 0.0087 1.0000 0.9544
-1.250 -0.1824 0.02691 0.01669 0.0020 1.0000 0.9732
-1.000 -0.1353 0.02708 0.01673 -0.0030 1.0000 0.9876
-0.750 -0.0898 0.02723 0.01675 -0.0080 0.9991 1.0000
-0.500 -0.0582 0.02725 0.01669 -0.0103 0.9918 1.0000
-0.250 -0.0275 0.02731 0.01668 -0.0124 0.9842 1.0000
0.000 0.0008 0.02736 0.01667 -0.0140 0.9758 1.0000
0.250 0.0296 0.02747 0.01673 -0.0155 0.9679 1.0000
0.500 0.0583 0.02760 0.01683 -0.0169 0.9595 1.0000
0.750 0.0835 0.02771 0.01691 -0.0175 0.9502 1.0000
1.000 0.1161 0.02794 0.01712 -0.0194 0.9428 1.0000
1.250 0.1382 0.02805 0.01723 -0.0193 0.9321 1.0000
1.500 0.1669 0.02825 0.01744 -0.0203 0.9233 1.0000
1.750 0.1954 0.02844 0.01765 -0.0212 0.9137 1.0000
2.000 0.2193 0.02861 0.01785 -0.0211 0.9028 1.0000
2.250 0.2558 0.02882 0.01811 -0.0232 0.8947 1.0000
2.500 0.2790 0.02895 0.01830 -0.0228 0.8821 1.0000
2.750 0.3047 0.02906 0.01848 -0.0228 0.8693 1.0000
3.000 0.3356 0.02906 0.01857 -0.0234 0.8559 1.0000
3.250 0.3699 0.02885 0.01847 -0.0242 0.8398 1.0000
3.500 0.4052 0.02839 0.01814 -0.0248 0.8206 1.0000
3.750 0.4457 0.02763 0.01755 -0.0258 0.8003 1.0000
4.000 0.4731 0.02700 0.01705 -0.0246 0.7773 1.0000
4.250 0.5035 0.02619 0.01638 -0.0235 0.7532 1.0000
4.500 0.5276 0.02554 0.01586 -0.0214 0.7253 1.0000
4.750 0.5571 0.02478 0.01522 -0.0201 0.6915 1.0000
5.000 0.5890 0.02407 0.01457 -0.0190 0.6445 1.0000
5.250 0.6298 0.02340 0.01375 -0.0191 0.5608 1.0000
5.500 0.6569 0.02366 0.01331 -0.0175 0.4364 1.0000
5.750 0.6627 0.02470 0.01369 -0.0134 0.3472 1.0000
6.000 0.6675 0.02586 0.01438 -0.0096 0.2879 1.0000
6.250 0.6753 0.02697 0.01516 -0.0065 0.2471 1.0000
6.500 0.6859 0.02807 0.01599 -0.0039 0.2171 1.0000
6.750 0.7006 0.02909 0.01690 -0.0019 0.1930 1.0000
7.000 0.7173 0.03014 0.01783 -0.0003 0.1738 1.0000
7.250 0.7375 0.03119 0.01884 0.0007 0.1580 1.0000
7.500 0.7614 0.03227 0.01991 0.0012 0.1441 1.0000
7.750 0.7883 0.03341 0.02107 0.0012 0.1322 1.0000
8.000 0.8150 0.03464 0.02225 0.0012 0.1226 1.0000
8.250 0.8407 0.03587 0.02361 0.0014 0.1136 1.0000
8.500 0.8679 0.03733 0.02514 0.0013 0.1065 1.0000
8.750 0.8907 0.03873 0.02667 0.0018 0.1000 1.0000
9.000 0.9150 0.04039 0.02838 0.0021 0.0950 1.0000
9.250 0.9345 0.04217 0.03046 0.0031 0.0900 1.0000
9.500 0.9526 0.04372 0.03206 0.0041 0.0860 1.0000
9.750 0.9693 0.04584 0.03441 0.0053 0.0828 1.0000
10.000 0.9795 0.04812 0.03707 0.0075 0.0796 1.0000
10.250 0.9890 0.05011 0.03928 0.0095 0.0767 1.0000
10.500 1.0007 0.05196 0.04119 0.0111 0.0743 1.0000
10.750 1.0062 0.05451 0.04397 0.0133 0.0727 1.0000
11.000 0.9978 0.05742 0.04731 0.0172 0.0714 1.0000
11.250 0.9855 0.06034 0.05059 0.0211 0.0702 1.0000
11.500 0.9709 0.06343 0.05398 0.0245 0.0692 1.0000
11.750 0.9542 0.06679 0.05760 0.0274 0.0684 1.0000
12.000 0.9343 0.07058 0.06163 0.0296 0.0678 1.0000
12.250 0.9097 0.07509 0.06638 0.0309 0.0675 1.0000
12.500 0.8774 0.08096 0.07248 0.0306 0.0677 1.0000
12.750 0.8356 0.08919 0.08091 0.0277 0.0685 1.0000
13.000 0.7897 0.10044 0.09229 0.0213 0.0697 1.0000
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Polar data table (+)
Polar graphs
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