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

LWK 80-080 (lwk80080-il)

LWK 80-080 - LWK 80-080 symmetrical airfoil


Airfoil lwk80080-il
Details Dat file Parser  
(lwk80080-il) LWK 80-080
LWK 80-080 symmetrical airfoil
Max thickness 8.1% at 40.2% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
LWK 80-080
1.00000     0.00000
0.99893     0.00084
0.99572     0.00112
0.99039     0.00158
0.98296     0.00208
0.97347     0.00273
0.96194     0.00351
0.94844     0.00444
0.93301     0.00554
0.91573     0.00686
0.89668     0.00843
0.87592     0.01025
0.85355     0.01236
0.82967     0.01476
0.80438     0.01744
0.77779     0.02032
0.75000     0.02329
0.72114     0.02624
0.69134     0.02907
0.66072     0.03169
0.62941     0.03400
0.59755     0.03593
0.56526     0.03746
0.53270     0.03863
0.50000     0.03946
0.46730     0.04000
0.43474     0.04028
0.40245     0.04031
0.37059     0.04011
0.33928     0.03968
0.30866     0.03905
0.27886     0.03820
0.25000     0.03716
0.22221     0.03594
0.19562     0.03453
0.17033     0.03296
0.14645     0.03122
0.12408     0.02934
0.10332     0.02730
0.08427     0.02514
0.06699     0.02284
0.05156     0.02040
0.03806     0.01782
0.02653     0.01506
0.01704     0.01215
0.00961     0.00911
0.00428     0.00600
0.00107     0.00296
0.00000     0.00000
0.00107     -0.00296
0.00428     -0.00600
0.00961     -0.00911
0.01704     -0.01215
0.02653     -0.01506
0.03806     -0.01782
0.05156     -0.02040
0.06699     -0.02284
0.08427     -0.02514
0.10332     -0.02730
0.12408     -0.02934
0.14645     -0.03122
0.17033     -0.03296
0.19562     -0.03453
0.22221     -0.03594
0.25000     -0.03716
0.27886     -0.03820
0.30866     -0.03905
0.33928     -0.03968
0.37059     -0.04011
0.40245     -0.04031
0.43474     -0.04028
0.46730     -0.04000
0.50000     -0.03946
0.53270     -0.03863
0.56526     -0.03746
0.59755     -0.03593
0.62941     -0.03400
0.66072     -0.03169
0.69134     -0.02907
0.72114     -0.02624
0.75000     -0.02329
0.77779     -0.02032
0.80438     -0.01744
0.82967     -0.01476
0.85355     -0.01236
0.87592     -0.01025
0.89668     -0.00843
0.91573     -0.00686
0.93301     -0.00554
0.94844     -0.00444
0.96194     -0.00351
0.97347     -0.00273
0.98296     -0.00208
0.99039     -0.00158
0.99572     -0.00112
0.99893     -0.00084
1.00000     0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

NACA 64-008A AIRFOILPreviewDetails
NACA 0008-34PreviewDetails
HQ 0/9 AIRFOILPreviewDetails
dh4009smPreviewDetails
HQ 0/7 AIRFOILPreviewDetails
NACA M2PreviewDetails
NACA M2 AIRFOILPreviewDetails
NACA 0008PreviewDetails
RAF 30 MOD AIRFOILPreviewDetails
NACA-0009 9.0% smoothedPreviewDetails

Polars for LWK 80-080 (lwk80080-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   lwk80080-il50,000922.4 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   lwk80080-il50,000524.7 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   lwk80080-il100,000937.4 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   lwk80080-il100,000533.9 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   lwk80080-il200,000945.9 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   lwk80080-il200,000535.7 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   lwk80080-il500,000947.2 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   lwk80080-il500,000547.2 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   lwk80080-il1,000,000954.1 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   lwk80080-il1,000,000557.2 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit