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LOCKHEED C-5A BL0 AIRFOIL (c5a-il)

LOCKHEED C-5A BL0 AIRFOIL - Lockheed-Georgia C-5A transonic wing airfoils


Airfoil c5a-il
Details Dat file Parser  
(c5a-il) LOCKHEED C-5A BL0 AIRFOIL
Lockheed-Georgia C-5A transonic wing airfoils
Max thickness 13.1% at 40% chord.
Max camber 0.7% at 85% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 LOCKHEED C-5A BL0 AIRFOIL
      31.0      31.0

 0.0000000 0.0000000
 0.0024662 0.0060003
 0.0049476 0.0093025
 0.0074333 0.0118483
 0.0099212 0.0139863
 0.0198849 0.0204449
 0.0398416 0.0281331
 0.0598078 0.0341333
 0.0797819 0.0387293
 0.0997602 0.0425716
 0.1197435 0.0455483
 0.1397268 0.0484987
 0.1597121 0.0511135
 0.1796996 0.0533356
 0.1996871 0.0555578
 0.2496638 0.0596990
 0.2996463 0.0627991
 0.3496348 0.0648375
 0.3996294 0.0658045
 0.4496279 0.0660632
 0.4996347 0.0648517
 0.5496448 0.0630606
 0.5996597 0.0604251
 0.6496783 0.0571130
 0.6997023 0.0528586
 0.7497316 0.0476611
 0.7997669 0.0413868
 0.8498083 0.0340335
 0.8998585 0.0251293
 0.9499188 0.0144084
 1.0000000 0.0012891

 0.0000000 0.0000000
 0.0025552 -.0098082
 0.0050712 -.0126413
 0.0075821 -.0145710
 0.0100912 -.0161904
 0.0201190 -.0211286
 0.0401606 -.0285220
 0.0601944 -.0345164
 0.0802217 -.0393713
 0.1002445 -.0434197
 0.1202620 -.0465232
 0.1402795 -.0496266
 0.1602948 -.0523492
 0.1803079 -.0546749
 0.2003210 -.0569919
 0.2503438 -.0610340
 0.3003593 -.0637928
 0.3503676 -.0652734
 0.4003684 -.0654090
 0.4503620 -.0642661
 0.5003483 -.0618453
 0.5503282 -.0582788
 0.6003021 -.0536345
 0.6502695 -.0478416
 0.7002328 -.0413427
 0.7501936 -.0343782
 0.8001516 -.0269141
 0.8501087 -.0193053
 0.9000686 -.0121834
 0.9500340 -.0060301
 1.0000000 -.0012891
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Lednicer format dat file
Selig format dat file

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Polars for LOCKHEED C-5A BL0 AIRFOIL (c5a-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   c5a-il50,000927.2 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   c5a-il50,000527.1 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   c5a-il100,000941.5 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   c5a-il100,000532.5 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   c5a-il200,000944.9 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   c5a-il200,000540.7 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   c5a-il500,000956.8 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   c5a-il500,000555.8 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   c5a-il1,000,000968.9 at α=10.75°Mach=0 Ncrit=9Xfoil predictionDetails
   c5a-il1,000,000572.3 at α=9.75°Mach=0 Ncrit=5Xfoil predictionDetails
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