Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

LOCKHEED C-5A BL1256 AIRFOIL (c5e-il)

LOCKHEED C-5A BL1256 AIRFOIL - Lockheed-Georgia C-5A transonic wing airfoils


Airfoil c5e-il
Details Dat file Parser  
(c5e-il) LOCKHEED C-5A BL1256 AIRFOIL
Lockheed-Georgia C-5A transonic wing airfoils
Max thickness 10.8% at 40% chord.
Max camber 1.4% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 LOCKHEED C-5A BL1256 AIRFOIL
      31.0      31.0

 0.0000000 0.0000000
 0.0024371 0.0084483
 0.0049088 0.0122368
 0.0073858 0.0153213
 0.0098689 0.0175894
 0.0198180 0.0244284
 0.0397596 0.0322660
 0.0597161 0.0380975
 0.0796853 0.0422430
 0.0996568 0.0460573
 0.1196355 0.0489262
 0.1396141 0.0517950
 0.1595954 0.0543012
 0.1795789 0.0565219
 0.1995625 0.0587235
 0.2495320 0.0628068
 0.2995097 0.0657993
 0.3495007 0.0670166
 0.3995006 0.0670274
 0.4495094 0.0658464
 0.4995279 0.0633623
 0.5495548 0.0597482
 0.5995877 0.0553360
 0.6496280 0.0499347
 0.6996742 0.0437337
 0.7497240 0.0370423
 0.7997734 0.0304147
 0.8498249 0.0235016
 0.8998758 0.0166663
 0.9499312 0.0092338
 1.0000000 0.0010067

 0.0000000 0.0000000
 0.0025730 -.0097998
 0.0051060 -.0142250
 0.0076241 -.0166560
 0.0101393 -.0187012
 0.0201757 -.0235780
 0.0402075 -.0278531
 0.0602251 -.0302092
 0.0802345 -.0314709
 0.1002394 -.0321283
 0.1202419 -.0324612
 0.1402438 -.0327204
 0.1602459 -.0330087
 0.1802485 -.0333514
 0.2002510 -.0336942
 0.2502619 -.0351537
 0.3002777 -.0372709
 0.3502946 -.0395440
 0.4003040 -.0408043
 0.4503021 -.0405429
 0.5002913 -.0391022
 0.5502720 -.0365084
 0.6002453 -.0329274
 0.6502142 -.0287522
 0.7001804 -.0242120
 0.7501462 -.0196191
 0.8001077 -.0144578
 0.8500722 -.0096938
 0.9000398 -.0053407
 0.9500177 -.0023792
 1.0000000 -.0010067
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

NACA 0012-64 a=0.8 c(li)=0.2PreviewDetails
KC-135 BL200.76 AIRFOILPreviewDetails
GIII BL45 AIRFOILPreviewDetails
NASA/LANGLEY RC-10(B)3 AIRFOILPreviewDetails
NASA/LANGLEY RC-10(N)1 AIRFOILPreviewDetails
BOEING 737 OUTBOARD AIRFOILPreviewDetails
NASA/LANGLEY RC10-64C AIRFOILPreviewDetails
GIII BL75 AIRFOILPreviewDetails
NASA RC(4)-10 AIRFOILPreviewDetails
BOEING-VERTOL VR-11X AIRFOILPreviewDetails

Polars for LOCKHEED C-5A BL1256 AIRFOIL (c5e-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   c5e-il50,000931.7 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   c5e-il50,000531.3 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   c5e-il100,000946.4 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   c5e-il100,000542.3 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   c5e-il200,000959.6 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   c5e-il200,000547.9 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   c5e-il500,000967.3 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   c5e-il500,000564.5 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   c5e-il1,000,000977.2 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   c5e-il1,000,000581 at α=9.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit