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

USA 5 AIRFOIL (usa5-il)

USA 5 AIRFOIL - USA-5 airfoil


Airfoil usa5-il
Details Dat file Parser  
(usa5-il) USA 5 AIRFOIL
USA-5 airfoil
Max thickness 6.4% at 30% chord.
Max camber 4.5% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
USA 5 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0137300
 0.0250000 0.0231600
 0.0500000 0.0370100
 0.0750000 0.0469700
 0.1000000 0.0551300
 0.1500000 0.0650400
 0.2000000 0.0725600
 0.3000000 0.0771900
 0.4000000 0.0753200
 0.5000000 0.0704500
 0.6000000 0.0616800
 0.7000000 0.0505100
 0.8000000 0.0365400
 0.9000000 0.0195700
 0.9500000 0.0098800
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0055700
 0.0250000 -.0069400
 0.0500000 -.0068800
 0.0750000 -.0046300
 0.1000000 -.0010700
 0.1500000 0.0045400
 0.2000000 0.0090600
 0.3000000 0.0133900
 0.4000000 0.0153200
 0.5000000 0.0132500
 0.6000000 0.0102800
 0.7000000 0.0059100
 0.8000000 0.0022400
 0.9000000 -.0012300
 0.9500000 -.0031200
 1.0000000 0.0000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

USA 41 AIRFOILPreviewDetails
GOE 210 (DAIMLER) AIRFOILPreviewDetails
GOE 372 AIRFOILPreviewDetails
GOE 403 AIRFOILPreviewDetails
GOE 269 AIRFOILPreviewDetails
GOE 399 AIRFOILPreviewDetails
GOE 377 AIRFOILPreviewDetails
GOE 373 AIRFOILPreviewDetails
GOE 371 AIRFOILPreviewDetails
GOE 517 AIRFOILPreviewDetails

Polars for USA 5 AIRFOIL (usa5-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   usa5-il50,000938.9 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   usa5-il50,000540.7 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   usa5-il100,000955.8 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   usa5-il100,000556.3 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   usa5-il200,000972.4 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   usa5-il200,000571 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   usa5-il500,000995 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   usa5-il500,000591.9 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   usa5-il1,000,0009112.5 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   usa5-il1,000,000599.7 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit