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

AH 80-136 (ah80136-il)

AH 80-136 - Althaus AH 80-136 airfoil


Airfoil ah80136-il
Details Dat file Parser  
(ah80136-il) AH 80-136
Althaus AH 80-136 airfoil
Max thickness 13.5% at 33.9% chord.
Max camber 3.4% at 33.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AH 80-136
1.00000     0.00146
0.99893     0.00146
0.99572     0.00144
0.99039     0.00123
0.98296     0.00098
0.97347     0.00083
0.96194     0.00096
0.94844     0.00146
0.93301     0.00232
0.91573     0.00355
0.89668     0.00525
0.87592     0.00757
0.85355     0.01058
0.82967     0.01429
0.80438     0.01868
0.77779     0.02374
0.75000     0.02948
0.72114     0.03588
0.69134     0.04290
0.66072     0.05042
0.62941     0.05823
0.59755     0.06616
0.56526     0.07398
0.53270     0.08141
0.50000     0.08802
0.46730     0.09344
0.43474     0.09749
0.40245     0.10017
0.37059     0.10156
0.33928     0.10177
0.30866     0.10093
0.27886     0.09918
0.25000     0.09659
0.22221     0.09316
0.19562     0.08890
0.17033     0.08388
0.14645     0.07824
0.12408     0.07204
0.10332     0.06536
0.08427     0.05829
0.06699     0.05097
0.05156     0.04361
0.03806     0.03635
0.02653     0.02929
0.01704     0.02243
0.00961     0.01583
0.00428     0.00972
0.00107     0.00441
0.00000     0.00000
0.00107     -0.00373
0.00428     -0.00707
0.00961     -0.01008
0.01704     -0.01270
0.02653     -0.01495
0.03806     -0.01703
0.05156     -0.01913
0.06699     -0.02124
0.08427     -0.02326
0.10332     -0.02510
0.12408     -0.02673
0.14645     -0.02817
0.17033     -0.02945
0.19562     -0.03058
0.22221     -0.03155
0.25000     -0.03233
0.27886     -0.03295
0.30866     -0.03342
0.33928     -0.03372
0.37059     -0.03382
0.40245     -0.03365
0.43474     -0.03318
0.46730     -0.03241
0.50000     -0.03136
0.53270     -0.03013
0.56526     -0.02885
0.59755     -0.02756
0.62941     -0.02625
0.66072     -0.02491
0.69134     -0.02353
0.72114     -0.02205
0.75000     -0.02043
0.77779     -0.01865
0.80438     -0.01682
0.82967     -0.01504
0.85355     -0.01334
0.87592     -0.01168
0.89668     -0.00999
0.91573     -0.00828
0.93301     -0.00666
0.94844     -0.00524
0.96194     -0.00402
0.97347     -0.00296
0.98296     -0.00201
0.99039     -0.00123
0.99572     -0.00061
0.99893     -0.00049
1.00000     -0.00029
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

MRC-16PreviewDetails
GOE 575 AIRFOILPreviewDetails
FX 63-143 AIRFOILPreviewDetails
BOEING 106 AIRFOILPreviewDetails
EPPLER 338 AIRFOILPreviewDetails
EPPLER 329 AIRFOILPreviewDetails
FX 84-W-127PreviewDetails
GOE 629 AIRFOILPreviewDetails
FX 61-140 AIRFOILPreviewDetails
GOE 632 AIRFOILPreviewDetails

Polars for AH 80-136 (ah80136-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ah80136-il50,000914.9 at α=14°Mach=0 Ncrit=9Xfoil predictionDetails
   ah80136-il50,000513.8 at α=12.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ah80136-il100,000932.2 at α=11°Mach=0 Ncrit=9Xfoil predictionDetails
   ah80136-il100,000533.4 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ah80136-il200,000971 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ah80136-il200,000571.2 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ah80136-il500,0009110.4 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ah80136-il500,0005105.4 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ah80136-il1,000,0009138.8 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ah80136-il1,000,0005127.6 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit