LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il) Reynolds number: 50,000 Max Cl/Cd: 31.83 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141e-il-50000-n5.txt Download as CSV file: xf-c141e-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5450 0.08815 0.08031 -0.0468 1.0000 0.0684
-9.000 -0.5591 0.08465 0.07685 -0.0459 1.0000 0.0682
-8.750 -0.5725 0.08082 0.07302 -0.0452 1.0000 0.0681
-8.500 -0.5858 0.07698 0.06914 -0.0442 1.0000 0.0681
-8.250 -0.5980 0.07311 0.06517 -0.0429 1.0000 0.0681
-8.000 -0.6081 0.06922 0.06114 -0.0414 1.0000 0.0682
-7.750 -0.6152 0.06536 0.05708 -0.0397 1.0000 0.0683
-7.500 -0.6185 0.06160 0.05307 -0.0379 1.0000 0.0683
-7.250 -0.6185 0.05793 0.04911 -0.0361 1.0000 0.0684
-7.000 -0.6125 0.05490 0.04594 -0.0344 1.0000 0.0689
-6.750 -0.6028 0.05266 0.04364 -0.0329 1.0000 0.0701
-6.500 -0.5929 0.05039 0.04120 -0.0313 1.0000 0.0718
-6.250 -0.5826 0.04781 0.03833 -0.0298 1.0000 0.0736
-6.000 -0.5708 0.04505 0.03520 -0.0283 1.0000 0.0750
-5.750 -0.5568 0.04233 0.03204 -0.0268 1.0000 0.0761
-5.500 -0.5407 0.03982 0.02903 -0.0254 1.0000 0.0780
-5.250 -0.5229 0.03774 0.02658 -0.0243 1.0000 0.0806
-5.000 -0.5038 0.03626 0.02501 -0.0233 1.0000 0.0832
-4.750 -0.4832 0.03464 0.02314 -0.0223 1.0000 0.0857
-4.500 -0.4616 0.03315 0.02132 -0.0213 1.0000 0.0892
-4.250 -0.4391 0.03179 0.01963 -0.0204 1.0000 0.0933
-4.000 -0.4168 0.03066 0.01846 -0.0197 1.0000 0.0971
-3.750 -0.3934 0.02967 0.01732 -0.0190 1.0000 0.1022
-3.500 -0.3695 0.02873 0.01621 -0.0182 1.0000 0.1080
-3.250 -0.3461 0.02792 0.01542 -0.0175 1.0000 0.1141
-3.000 -0.3222 0.02727 0.01461 -0.0167 1.0000 0.1223
-2.750 -0.2986 0.02657 0.01398 -0.0161 1.0000 0.1307
-2.500 -0.2750 0.02601 0.01336 -0.0155 1.0000 0.1414
-2.250 -0.2521 0.02552 0.01280 -0.0147 1.0000 0.1542
-2.000 -0.2295 0.02499 0.01234 -0.0141 1.0000 0.1703
-1.750 -0.2067 0.02443 0.01196 -0.0137 1.0000 0.1932
-1.500 -0.1831 0.02374 0.01160 -0.0136 1.0000 0.2401
-1.250 -0.1670 0.02155 0.01178 -0.0109 1.0000 0.6774
-1.000 -0.1173 0.02149 0.01211 -0.0133 1.0000 1.0000
-0.750 -0.0893 0.02174 0.01207 -0.0141 0.9963 1.0000
-0.500 -0.0548 0.02208 0.01215 -0.0161 0.9902 1.0000
-0.250 -0.0193 0.02248 0.01232 -0.0183 0.9843 1.0000
0.000 0.0132 0.02280 0.01247 -0.0199 0.9771 1.0000
0.250 0.0488 0.02322 0.01274 -0.0221 0.9711 1.0000
0.500 0.0800 0.02354 0.01295 -0.0234 0.9631 1.0000
0.750 0.1146 0.02394 0.01326 -0.0253 0.9563 1.0000
1.000 0.1459 0.02428 0.01354 -0.0266 0.9480 1.0000
1.250 0.1789 0.02465 0.01387 -0.0282 0.9402 1.0000
1.500 0.2118 0.02501 0.01421 -0.0297 0.9317 1.0000
1.750 0.2421 0.02534 0.01454 -0.0306 0.9224 1.0000
2.000 0.2790 0.02569 0.01491 -0.0328 0.9144 1.0000
2.250 0.3076 0.02596 0.01522 -0.0333 0.9029 1.0000
2.500 0.3426 0.02611 0.01543 -0.0347 0.8897 1.0000
2.750 0.3862 0.02585 0.01526 -0.0369 0.8709 1.0000
3.000 0.4354 0.02525 0.01479 -0.0396 0.8511 1.0000
3.250 0.4680 0.02492 0.01458 -0.0396 0.8311 1.0000
3.500 0.5014 0.02462 0.01442 -0.0398 0.8134 1.0000
3.750 0.5333 0.02426 0.01422 -0.0395 0.7939 1.0000
4.000 0.5705 0.02357 0.01368 -0.0396 0.7702 1.0000
4.250 0.5977 0.02291 0.01315 -0.0376 0.7338 1.0000
4.500 0.6260 0.02225 0.01255 -0.0357 0.6828 1.0000
4.750 0.6586 0.02173 0.01193 -0.0345 0.6104 1.0000
5.000 0.6917 0.02173 0.01137 -0.0334 0.4863 1.0000
5.250 0.7058 0.02279 0.01165 -0.0304 0.3755 1.0000
5.500 0.7167 0.02408 0.01239 -0.0276 0.3059 1.0000
5.750 0.7301 0.02532 0.01328 -0.0254 0.2581 1.0000
6.000 0.7459 0.02652 0.01424 -0.0236 0.2223 1.0000
6.250 0.7638 0.02768 0.01523 -0.0222 0.1943 1.0000
6.500 0.7838 0.02879 0.01624 -0.0210 0.1718 1.0000
6.750 0.8052 0.02986 0.01728 -0.0201 0.1530 1.0000
7.000 0.8277 0.03094 0.01833 -0.0194 0.1375 1.0000
7.250 0.8512 0.03206 0.01945 -0.0188 0.1249 1.0000
7.500 0.8748 0.03327 0.02060 -0.0183 0.1150 1.0000
7.750 0.8996 0.03455 0.02197 -0.0178 0.1061 1.0000
8.000 0.9261 0.03608 0.02359 -0.0177 0.0991 1.0000
8.250 0.9494 0.03754 0.02511 -0.0172 0.0930 1.0000
8.500 0.9743 0.03937 0.02705 -0.0169 0.0884 1.0000
8.750 0.9966 0.04136 0.02934 -0.0162 0.0843 1.0000
9.000 1.0162 0.04312 0.03120 -0.0153 0.0806 1.0000
9.250 1.0346 0.04519 0.03338 -0.0144 0.0777 1.0000
9.500 1.0476 0.04777 0.03645 -0.0126 0.0752 1.0000
9.750 1.0584 0.05046 0.03952 -0.0107 0.0734 1.0000
10.000 1.0669 0.05299 0.04235 -0.0088 0.0715 1.0000
10.250 1.0751 0.05531 0.04484 -0.0069 0.0697 1.0000
10.500 1.0854 0.05756 0.04714 -0.0055 0.0680 1.0000
10.750 1.0790 0.06080 0.05079 -0.0024 0.0670 1.0000
11.000 1.0650 0.06422 0.05461 0.0012 0.0664 1.0000
11.250 1.0474 0.06779 0.05851 0.0046 0.0660 1.0000
11.500 1.0266 0.07178 0.06278 0.0073 0.0659 1.0000
11.750 1.0024 0.07634 0.06759 0.0088 0.0658 1.0000
12.000 0.9750 0.08172 0.07318 0.0089 0.0660 1.0000
12.250 0.9446 0.08827 0.07992 0.0071 0.0662 1.0000
12.500 0.9127 0.09635 0.08814 0.0032 0.0666 1.0000
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Polar data table (+)
Polar graphs
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