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

CLARK Z AIRFOIL (clarkz-il)

CLARK Z AIRFOIL - CLARK Z airfoil


Airfoil clarkz-il
Details Dat file Parser  
(clarkz-il) CLARK Z AIRFOIL
CLARK Z airfoil
Max thickness 11.8% at 30% chord.
Max camber 4% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
CLARK Z AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0239500
 0.0250000 0.0355900
 0.0500000 0.0506800
 0.0750000 0.0609700
 0.1000000 0.0693600
 0.1500000 0.0820400
 0.2000000 0.0905200
 0.3000000 0.0981800
 0.4000000 0.0977400
 0.5000000 0.0916000
 0.6000000 0.0804600
 0.7000000 0.0652200
 0.8000000 0.0466800
 0.9000000 0.0252400
 0.9500000 0.0135200
 1.0000000 0.0012000

 0.0000000 0.0000000
 0.0125000 -.0169600
 0.0250000 -.0207100
 0.0500000 -.0235200
 0.0750000 -.0245300
 0.1000000 -.0245400
 0.1500000 -.0234600
 0.2000000 -.0220800
 0.3000000 -.0193200
 0.4000000 -.0165600
 0.5000000 -.0138000
 0.6000000 -.0110400
 0.7000000 -.0082800
 0.8000000 -.0055200
 0.9000000 -.0027600
 0.9500000 -.0013800
 1.0000000 0.0000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

Rhode St. Genese 32PreviewDetails
GOE 593 AIRFOILPreviewDetails
NACA 4412PreviewDetails
GOE 479 AIRFOILPreviewDetails
USA-35B AIRFOILPreviewDetails
GOE 623 AIRFOILPreviewDetails
GOE 693 AIRFOILPreviewDetails
GOE 796 AIRFOILPreviewDetails
GOE 526 AIRFOILPreviewDetails
Davis AIRFOILPreviewDetails

Polars for CLARK Z AIRFOIL (clarkz-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   clarkz-il50,000930.4 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   clarkz-il50,000536.2 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   clarkz-il100,000954 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   clarkz-il100,000555.4 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   clarkz-il200,000974.8 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   clarkz-il200,000572.2 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   clarkz-il500,0009100.9 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   clarkz-il500,000593.5 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   clarkz-il1,000,0009120.6 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   clarkz-il1,000,0005109.5 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit