LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il) Reynolds number: 50,000 Max Cl/Cd: 33.37 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141e-il-50000.txt Download as CSV file: xf-c141e-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4457 0.11067 0.10293 -0.0191 1.0000 0.2785
-9.000 -0.4728 0.11030 0.10272 -0.0190 1.0000 0.2898
-8.750 -0.4583 0.10650 0.09893 -0.0172 1.0000 0.3060
-8.500 -0.4452 0.10286 0.09531 -0.0156 1.0000 0.3213
-8.250 -0.4389 0.09978 0.09228 -0.0140 1.0000 0.3366
-8.000 -0.4380 0.09721 0.08977 -0.0121 1.0000 0.3543
-7.750 -0.4471 0.09543 0.08810 -0.0097 1.0000 0.3742
-7.500 -0.4648 0.09419 0.08699 -0.0065 1.0000 0.3928
-7.250 -0.4383 0.09055 0.08332 -0.0039 1.0000 0.4255
-7.000 -0.4141 0.08694 0.07970 -0.0017 1.0000 0.4553
-6.750 -0.4049 0.08426 0.07707 0.0010 1.0000 0.4846
-6.500 -0.3921 0.08166 0.07449 0.0039 1.0000 0.5191
-6.250 -0.3856 0.07984 0.07271 0.0078 1.0000 0.5610
-6.000 -0.3597 0.07640 0.06926 0.0094 1.0000 0.6016
-5.000 -0.5243 0.04689 0.03811 -0.0222 1.0000 0.1816
-4.750 -0.5052 0.04350 0.03371 -0.0219 1.0000 0.1709
-4.500 -0.4854 0.04075 0.03062 -0.0211 1.0000 0.1705
-4.250 -0.4638 0.03818 0.02770 -0.0204 1.0000 0.1699
-4.000 -0.4408 0.03601 0.02509 -0.0197 1.0000 0.1704
-3.750 -0.4180 0.03385 0.02285 -0.0191 1.0000 0.1749
-3.500 -0.3936 0.03219 0.02097 -0.0185 1.0000 0.1794
-3.250 -0.3678 0.03080 0.01919 -0.0180 1.0000 0.1855
-3.000 -0.3424 0.02934 0.01766 -0.0175 1.0000 0.1939
-2.750 -0.3163 0.02832 0.01637 -0.0169 1.0000 0.2042
-2.500 -0.2904 0.02715 0.01527 -0.0164 1.0000 0.2180
-2.250 -0.2638 0.02619 0.01433 -0.0158 1.0000 0.2362
-2.000 -0.2372 0.02524 0.01351 -0.0154 1.0000 0.2605
-1.750 -0.2118 0.02423 0.01278 -0.0149 1.0000 0.3002
-1.500 -0.1483 0.02131 0.01265 -0.0168 1.0000 1.0000
-1.250 -0.1332 0.02138 0.01230 -0.0149 1.0000 1.0000
-1.000 -0.1173 0.02149 0.01211 -0.0133 1.0000 1.0000
-0.750 -0.1005 0.02165 0.01201 -0.0119 1.0000 1.0000
-0.500 -0.0828 0.02185 0.01200 -0.0108 1.0000 1.0000
-0.250 -0.0645 0.02210 0.01206 -0.0097 1.0000 1.0000
0.000 -0.0458 0.02238 0.01218 -0.0088 1.0000 1.0000
0.250 -0.0268 0.02270 0.01236 -0.0080 1.0000 1.0000
0.500 -0.0075 0.02307 0.01261 -0.0073 1.0000 1.0000
0.750 0.0119 0.02347 0.01291 -0.0066 1.0000 1.0000
1.000 0.0313 0.02391 0.01327 -0.0061 1.0000 1.0000
1.250 0.0508 0.02440 0.01368 -0.0055 1.0000 1.0000
1.500 0.0702 0.02492 0.01416 -0.0051 1.0000 1.0000
1.750 0.0895 0.02549 0.01469 -0.0047 1.0000 1.0000
2.000 0.1086 0.02611 0.01529 -0.0043 1.0000 1.0000
2.250 0.1276 0.02677 0.01595 -0.0040 1.0000 1.0000
2.500 0.1463 0.02749 0.01667 -0.0038 1.0000 1.0000
2.750 0.1648 0.02827 0.01747 -0.0036 1.0000 1.0000
3.000 0.1828 0.02911 0.01835 -0.0035 1.0000 1.0000
3.250 0.2005 0.03002 0.01931 -0.0034 1.0000 1.0000
3.500 0.2541 0.03174 0.02115 -0.0101 0.9847 1.0000
3.750 0.3275 0.03322 0.02284 -0.0198 0.9497 1.0000
4.000 0.3895 0.03409 0.02393 -0.0264 0.9190 1.0000
4.250 0.4506 0.03437 0.02449 -0.0320 0.8871 1.0000
4.500 0.5255 0.03343 0.02390 -0.0378 0.8489 1.0000
4.750 0.6065 0.03020 0.02114 -0.0411 0.7982 1.0000
5.000 0.6783 0.02607 0.01751 -0.0412 0.7418 1.0000
5.250 0.7392 0.02215 0.01329 -0.0374 0.5663 1.0000
5.500 0.7547 0.02408 0.01347 -0.0328 0.3910 1.0000
5.750 0.7790 0.02635 0.01500 -0.0318 0.3128 1.0000
6.000 0.8096 0.02833 0.01661 -0.0319 0.2664 1.0000
6.250 0.8390 0.03021 0.01828 -0.0319 0.2348 1.0000
6.500 0.8667 0.03208 0.02004 -0.0317 0.2114 1.0000
6.750 0.8934 0.03409 0.02200 -0.0313 0.1937 1.0000
7.000 0.9166 0.03614 0.02425 -0.0303 0.1805 1.0000
7.250 0.9389 0.03852 0.02685 -0.0292 0.1710 1.0000
7.500 0.9616 0.04070 0.02909 -0.0284 0.1621 1.0000
7.750 0.9785 0.04358 0.03236 -0.0266 0.1576 1.0000
8.000 0.9908 0.04641 0.03569 -0.0242 0.1537 1.0000
8.250 1.0044 0.04912 0.03867 -0.0223 0.1494 1.0000
8.500 1.0256 0.05238 0.04182 -0.0219 0.1452 1.0000
8.750 1.0312 0.05596 0.04587 -0.0192 0.1448 1.0000
9.000 1.0341 0.05983 0.05016 -0.0165 0.1447 1.0000
9.250 1.0337 0.06388 0.05458 -0.0139 0.1448 1.0000
9.500 1.0311 0.06813 0.05914 -0.0114 0.1450 1.0000
9.750 0.9657 0.07430 0.06618 -0.0053 0.1534 1.0000
10.000 0.9427 0.07934 0.07138 -0.0031 0.1562 1.0000
10.250 0.9289 0.08444 0.07655 -0.0019 0.1585 1.0000
10.500 0.9298 0.08969 0.08187 -0.0017 0.1608 1.0000
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Polar data table (+)
Polar graphs
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