LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il) Reynolds number: 50,000 Max Cl/Cd: 30.75 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c5d-il-50000.txt Download as CSV file: xf-c5d-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-5A BL758.6 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4589 0.10823 0.10064 -0.0177 1.0000 0.3087
-8.750 -0.4622 0.10569 0.09818 -0.0166 1.0000 0.3230
-8.500 -0.4616 0.10301 0.09555 -0.0151 1.0000 0.3386
-8.250 -0.4590 0.10021 0.09281 -0.0135 1.0000 0.3546
-7.750 -0.4506 0.09449 0.08719 -0.0099 1.0000 0.3877
-7.250 -0.4452 0.08951 0.08232 -0.0051 1.0000 0.4292
-6.500 -0.6317 0.06055 0.05270 -0.0285 1.0000 0.1603
-6.250 -0.6296 0.05513 0.04680 -0.0277 1.0000 0.1484
-6.000 -0.6180 0.05145 0.04282 -0.0265 1.0000 0.1439
-5.750 -0.6057 0.04771 0.03877 -0.0253 1.0000 0.1402
-5.500 -0.5918 0.04389 0.03436 -0.0241 1.0000 0.1360
-5.250 -0.5746 0.04100 0.03105 -0.0229 1.0000 0.1366
-5.000 -0.5556 0.03858 0.02827 -0.0218 1.0000 0.1402
-4.750 -0.5343 0.03617 0.02538 -0.0208 1.0000 0.1433
-4.500 -0.5109 0.03403 0.02263 -0.0197 1.0000 0.1467
-4.250 -0.4880 0.03209 0.02077 -0.0190 1.0000 0.1559
-4.000 -0.4628 0.03028 0.01865 -0.0182 1.0000 0.1648
-3.750 -0.4373 0.02877 0.01704 -0.0175 1.0000 0.1793
-3.500 -0.4113 0.02729 0.01566 -0.0168 1.0000 0.1988
-3.250 -0.3853 0.02587 0.01441 -0.0160 1.0000 0.2320
-3.000 -0.3599 0.02387 0.01291 -0.0152 1.0000 0.3058
-2.750 -0.3563 0.02100 0.01293 -0.0075 1.0000 0.7107
-2.500 -0.1367 0.02405 0.01481 -0.0318 1.0000 1.0000
-2.250 -0.1363 0.02362 0.01426 -0.0285 1.0000 1.0000
-2.000 -0.1361 0.02322 0.01374 -0.0251 1.0000 1.0000
-1.750 -0.1359 0.02286 0.01328 -0.0216 1.0000 1.0000
-1.500 -0.1354 0.02254 0.01285 -0.0181 1.0000 1.0000
-1.250 -0.1339 0.02225 0.01247 -0.0147 1.0000 1.0000
-1.000 -0.1304 0.02204 0.01214 -0.0115 1.0000 1.0000
-0.750 -0.1239 0.02192 0.01188 -0.0088 1.0000 1.0000
-0.500 -0.1133 0.02190 0.01171 -0.0068 1.0000 1.0000
-0.250 -0.0993 0.02197 0.01165 -0.0053 1.0000 1.0000
0.000 -0.0833 0.02213 0.01168 -0.0042 1.0000 1.0000
0.250 -0.0659 0.02235 0.01179 -0.0033 1.0000 1.0000
0.500 -0.0476 0.02263 0.01196 -0.0026 1.0000 1.0000
0.750 -0.0288 0.02297 0.01220 -0.0020 1.0000 1.0000
1.000 -0.0097 0.02335 0.01251 -0.0016 1.0000 1.0000
1.250 0.0096 0.02378 0.01288 -0.0012 1.0000 1.0000
1.500 0.0290 0.02426 0.01331 -0.0008 1.0000 1.0000
1.750 0.0484 0.02478 0.01381 -0.0006 1.0000 1.0000
2.000 0.0677 0.02536 0.01437 -0.0003 1.0000 1.0000
2.250 0.0869 0.02599 0.01499 -0.0002 1.0000 1.0000
2.500 0.1058 0.02667 0.01567 -0.0001 1.0000 1.0000
2.750 0.1246 0.02740 0.01643 0.0000 1.0000 1.0000
3.000 0.1430 0.02820 0.01726 0.0000 1.0000 1.0000
3.250 0.1611 0.02906 0.01817 0.0000 1.0000 1.0000
3.500 0.1788 0.02999 0.01915 -0.0001 1.0000 1.0000
3.750 0.2040 0.03117 0.02042 -0.0018 0.9965 1.0000
4.000 0.2726 0.03316 0.02262 -0.0114 0.9703 1.0000
4.250 0.3353 0.03452 0.02421 -0.0190 0.9396 1.0000
4.500 0.4146 0.03518 0.02519 -0.0279 0.9031 1.0000
4.750 0.4743 0.03475 0.02508 -0.0322 0.8638 1.0000
5.000 0.5481 0.03290 0.02366 -0.0363 0.8211 1.0000
5.250 0.6229 0.02948 0.02078 -0.0382 0.7764 1.0000
5.500 0.6962 0.02366 0.01541 -0.0351 0.6871 1.0000
5.750 0.7213 0.02346 0.01324 -0.0277 0.3862 1.0000
6.000 0.7346 0.02605 0.01473 -0.0250 0.2868 1.0000
6.250 0.7720 0.02825 0.01652 -0.0262 0.2391 1.0000
6.500 0.8109 0.03025 0.01827 -0.0278 0.2140 1.0000
6.750 0.8444 0.03215 0.02017 -0.0285 0.1981 1.0000
7.000 0.8764 0.03422 0.02235 -0.0289 0.1883 1.0000
7.250 0.9028 0.03644 0.02486 -0.0285 0.1806 1.0000
7.500 0.9277 0.03859 0.02713 -0.0279 0.1727 1.0000
7.750 0.9510 0.04142 0.03020 -0.0272 0.1687 1.0000
8.000 0.9658 0.04399 0.03333 -0.0250 0.1653 1.0000
8.250 0.9794 0.04664 0.03637 -0.0230 0.1608 1.0000
8.500 0.9940 0.04963 0.03967 -0.0212 0.1579 1.0000
8.750 1.0141 0.05349 0.04352 -0.0207 0.1547 1.0000
9.000 1.0134 0.05679 0.04742 -0.0172 0.1536 1.0000
9.250 1.0109 0.06054 0.05165 -0.0141 0.1530 1.0000
9.500 1.0103 0.06485 0.05630 -0.0116 0.1536 1.0000
9.750 1.0092 0.06945 0.06116 -0.0095 0.1542 1.0000
10.000 0.9482 0.07511 0.06753 -0.0042 0.1633 1.0000
10.250 0.9298 0.08028 0.07283 -0.0025 0.1669 1.0000
10.500 0.9313 0.08576 0.07835 -0.0021 0.1693 1.0000
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Polar data table (+)
Polar graphs
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