LOCKHEED C-5A BL1256 AIRFOIL (c5e-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: LOCKHEED C-5A BL1256 AIRFOIL (c5e-il) Reynolds number: 50,000 Max Cl/Cd: 31.34 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c5e-il-50000-n5.txt Download as CSV file: xf-c5e-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-5A BL1256 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5086 0.12197 0.11401 -0.0081 1.0000 0.1309
-10.000 -0.5069 0.11821 0.11028 -0.0099 1.0000 0.1315
-9.500 -0.5390 0.10065 0.09270 -0.0261 1.0000 0.0784
-9.250 -0.5289 0.09722 0.08930 -0.0255 1.0000 0.0774
-9.000 -0.5276 0.09282 0.08493 -0.0274 1.0000 0.0765
-8.750 -0.5321 0.08788 0.08003 -0.0306 1.0000 0.0759
-8.500 -0.5409 0.08324 0.07541 -0.0332 1.0000 0.0755
-8.250 -0.5486 0.07878 0.07093 -0.0352 1.0000 0.0753
-8.000 -0.5543 0.07442 0.06651 -0.0366 1.0000 0.0753
-7.750 -0.5577 0.07023 0.06222 -0.0375 1.0000 0.0753
-7.500 -0.5586 0.06620 0.05804 -0.0378 1.0000 0.0751
-7.250 -0.5569 0.06231 0.05398 -0.0377 1.0000 0.0747
-7.000 -0.5530 0.05859 0.05007 -0.0373 1.0000 0.0744
-6.750 -0.5472 0.05507 0.04631 -0.0366 1.0000 0.0743
-6.500 -0.5394 0.05174 0.04272 -0.0356 1.0000 0.0744
-6.250 -0.5299 0.04868 0.03934 -0.0345 1.0000 0.0753
-6.000 -0.5191 0.04573 0.03598 -0.0333 1.0000 0.0769
-5.750 -0.5065 0.04292 0.03267 -0.0320 1.0000 0.0783
-5.500 -0.4917 0.04063 0.03019 -0.0307 1.0000 0.0793
-5.250 -0.4756 0.03868 0.02810 -0.0295 1.0000 0.0802
-5.000 -0.4589 0.03691 0.02614 -0.0283 1.0000 0.0813
-4.750 -0.4416 0.03532 0.02437 -0.0271 1.0000 0.0828
-4.500 -0.4236 0.03395 0.02281 -0.0259 1.0000 0.0856
-4.250 -0.4046 0.03254 0.02111 -0.0247 1.0000 0.0889
-4.000 -0.3842 0.03114 0.01932 -0.0235 1.0000 0.0913
-3.750 -0.3644 0.02993 0.01812 -0.0226 1.0000 0.0933
-3.500 -0.3444 0.02902 0.01718 -0.0216 1.0000 0.0963
-3.250 -0.3238 0.02826 0.01633 -0.0206 1.0000 0.1011
-3.000 -0.2993 0.02744 0.01534 -0.0200 0.9989 0.1062
-2.750 -0.2629 0.02658 0.01455 -0.0218 0.9927 0.1118
-2.500 -0.2266 0.02593 0.01378 -0.0234 0.9856 0.1213
-2.250 -0.1919 0.02526 0.01317 -0.0250 0.9786 0.1317
-2.000 -0.1560 0.02459 0.01254 -0.0268 0.9716 0.1452
-1.750 -0.1232 0.02397 0.01197 -0.0283 0.9630 0.1644
-1.500 -0.0872 0.02327 0.01138 -0.0306 0.9560 0.1930
-1.250 -0.0550 0.02235 0.01075 -0.0324 0.9472 0.2434
-1.000 -0.0368 0.02047 0.01113 -0.0298 0.9410 0.7020
-0.750 -0.0181 0.02072 0.01153 -0.0259 0.9311 0.8077
-0.500 0.0090 0.02094 0.01175 -0.0240 0.9232 0.8690
-0.250 0.0457 0.02109 0.01183 -0.0244 0.9158 0.9168
0.000 0.1096 0.02122 0.01185 -0.0305 0.9124 0.9582
0.250 0.2102 0.02123 0.01173 -0.0444 0.9128 1.0000
0.500 0.2364 0.02126 0.01170 -0.0449 0.9006 1.0000
0.750 0.2651 0.02129 0.01169 -0.0457 0.8898 1.0000
1.000 0.2941 0.02132 0.01169 -0.0464 0.8793 1.0000
1.250 0.3150 0.02145 0.01180 -0.0457 0.8666 1.0000
1.500 0.3383 0.02158 0.01193 -0.0453 0.8552 1.0000
1.750 0.3669 0.02166 0.01201 -0.0456 0.8455 1.0000
2.000 0.3858 0.02191 0.01226 -0.0445 0.8328 1.0000
2.250 0.4094 0.02215 0.01252 -0.0439 0.8217 1.0000
2.500 0.4396 0.02226 0.01267 -0.0443 0.8122 1.0000
2.750 0.4628 0.02245 0.01290 -0.0434 0.7981 1.0000
3.000 0.4900 0.02243 0.01293 -0.0426 0.7820 1.0000
3.250 0.5209 0.02205 0.01257 -0.0415 0.7617 1.0000
3.500 0.5428 0.02179 0.01233 -0.0391 0.7341 1.0000
3.750 0.5660 0.02140 0.01195 -0.0366 0.7033 1.0000
4.000 0.5879 0.02108 0.01162 -0.0341 0.6695 1.0000
4.250 0.6100 0.02096 0.01153 -0.0321 0.6370 1.0000
4.500 0.6319 0.02081 0.01137 -0.0299 0.5949 1.0000
4.750 0.6510 0.02077 0.01116 -0.0271 0.5252 1.0000
5.000 0.6654 0.02131 0.01088 -0.0237 0.3779 1.0000
5.250 0.6732 0.02309 0.01157 -0.0209 0.2461 1.0000
5.500 0.6869 0.02466 0.01268 -0.0194 0.1967 1.0000
5.750 0.7030 0.02603 0.01380 -0.0181 0.1721 1.0000
6.000 0.7211 0.02725 0.01493 -0.0169 0.1556 1.0000
6.250 0.7404 0.02844 0.01603 -0.0158 0.1430 1.0000
6.500 0.7611 0.02959 0.01710 -0.0149 0.1326 1.0000
6.750 0.7851 0.03070 0.01829 -0.0142 0.1242 1.0000
7.000 0.8106 0.03193 0.01943 -0.0138 0.1184 1.0000
7.250 0.8383 0.03314 0.02078 -0.0136 0.1125 1.0000
7.500 0.8642 0.03439 0.02206 -0.0133 0.1069 1.0000
7.750 0.8911 0.03583 0.02356 -0.0132 0.1026 1.0000
8.000 0.9180 0.03748 0.02541 -0.0130 0.0992 1.0000
8.250 0.9426 0.03911 0.02715 -0.0127 0.0958 1.0000
8.500 0.9667 0.04080 0.02878 -0.0125 0.0927 1.0000
8.750 0.9862 0.04290 0.03135 -0.0116 0.0895 1.0000
9.000 1.0052 0.04522 0.03399 -0.0108 0.0873 1.0000
9.250 1.0228 0.04743 0.03644 -0.0100 0.0849 1.0000
9.500 1.0401 0.04947 0.03860 -0.0094 0.0824 1.0000
9.750 1.0539 0.05204 0.04136 -0.0084 0.0804 1.0000
10.000 1.0578 0.05531 0.04515 -0.0066 0.0790 1.0000
10.250 1.0582 0.05873 0.04902 -0.0049 0.0777 1.0000
10.500 1.0546 0.06219 0.05287 -0.0031 0.0764 1.0000
10.750 1.0474 0.06569 0.05668 -0.0014 0.0752 1.0000
11.000 1.0351 0.06921 0.06045 0.0004 0.0743 1.0000
11.250 1.0172 0.07314 0.06462 0.0017 0.0738 1.0000
11.500 0.9922 0.07812 0.06983 0.0016 0.0737 1.0000
11.750 0.9564 0.08513 0.07708 -0.0009 0.0742 1.0000
12.000 0.9109 0.09537 0.08750 -0.0070 0.0753 1.0000
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Polar data table (+)
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