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 BL488.2 AIRFOIL (c5b-il)

LOCKHEED C-5A BL488.2 AIRFOIL - Lockheed-Georgia C-5A transonic wing airfoils


Airfoil c5b-il
Details Dat file Parser  
(c5b-il) LOCKHEED C-5A BL488.2 AIRFOIL
Lockheed-Georgia C-5A transonic wing airfoils
Max thickness 11.5% at 40% chord.
Max camber 1.2% at 70% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 LOCKHEED C-5A BL488.2 AIRFOIL
      31.0      31.0

 0.0000000 0.0000000
 0.0024659 0.0058770
 0.0049469 0.0091436
 0.0074314 0.0118045
 0.0099194 0.0138800
 0.0198817 0.0203586
 0.0398359 0.0282452
 0.0598005 0.0343399
 0.0797731 0.0390588
 0.0997515 0.0427696
 0.1197323 0.0460823
 0.1397147 0.0491068
 0.1596994 0.0517404
 0.1796862 0.0540166
 0.1996730 0.0562826
 0.2496481 0.0605668
 0.2996296 0.0637534
 0.3496169 0.0659417
 0.3996100 0.0671318
 0.4496083 0.0674223
 0.4996118 0.0668140
 0.5496212 0.0652075
 0.5996357 0.0627023
 0.6496549 0.0593981
 0.6996799 0.0550969
 0.7497113 0.0496983
 0.7997502 0.0430041
 0.8497968 0.0349791
 0.8998534 0.0252297
 0.9499178 0.0141421
 1.0000000 0.0011019

 0.0000000 0.0000000
 0.0025565 -.0097227
 0.0050746 -.0128480
 0.0075859 -.0147784
 0.0100950 -.0163595
 0.0201211 -.0208452
 0.0401552 -.0267133
 0.0601812 -.0311924
 0.0802010 -.0346046
 0.1002166 -.0372772
 0.1202276 -.0391819
 0.1402384 -.0410256
 0.1602476 -.0426161
 0.1802548 -.0438599
 0.2002620 -.0451036
 0.2502742 -.0471946
 0.3002807 -.0483178
 0.3502832 -.0487387
 0.4002810 -.0483625
 0.4502746 -.0472698
 0.5002637 -.0453804
 0.5502486 -.0427921
 0.6002295 -.0395050
 0.6502064 -.0355192
 0.7001786 -.0307432
 0.7501496 -.0257513
 0.8001195 -.0205656
 0.8500899 -.0154753
 0.9000604 -.0103920
 0.9500326 -.0056078
 1.0000000 -.0011019
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

LOCKHEED C-5A BL576 AIRFOILPreviewDetails
RAE 2822 AIRFOILPreviewDetails
RAE6-9CK AIRFOILPreviewDetails
RAE(NPL) 5212 AIRFOILPreviewDetails
NPL AIRFOIL FROM ARC CP 1372PreviewDetails
CAST 10-2/DOA 2 AIRFOILPreviewDetails
LOCKHEED C-5A BL758.6 AIRFOILPreviewDetails
LOCKHEED C-141 BL113.6 AIRFOILPreviewDetails
NYU/GRUMMAN K-1 AIRFOILPreviewDetails
NASA SC(2)-0412 AIRFOILPreviewDetails

Polars for LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   c5b-il50,000930.4 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   c5b-il50,000529.4 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   c5b-il100,000946.8 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   c5b-il100,000542.6 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   c5b-il200,000964.9 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   c5b-il200,000550.5 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   c5b-il500,000973.8 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   c5b-il500,000561.2 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   c5b-il1,000,000978.5 at α=1.75°Mach=0 Ncrit=9Xfoil predictionDetails
   c5b-il1,000,000577.1 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit