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AH 79-K-135/20 B (ah79k135-il)

AH 79-K-135/20 B - Althaus AH 79-K-135/20 airfoil for use with flaps (K)


Airfoil ah79k135-il
Details Dat file Parser  
(ah79k135-il) AH 79-K-135/20 B
Althaus AH 79-K-135/20 airfoil for use with flaps (K)
Max thickness 13.5% at 40.2% chord.
Max camber 3.1% at 40.2% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AH 79-K-135/20 B
1.00000     0.00000
0.99893     0.00038
0.99572     0.00142
0.99039     0.00280
0.98296     0.00440
0.97347     0.00629
0.96194     0.00841
0.94844     0.01077
0.93301     0.01340
0.91573     0.01630
0.89668     0.01942
0.87592     0.02273
0.85355     0.02640
0.82967     0.03051
0.80438     0.03571
0.77779     0.04278
0.75000     0.05094
0.72114     0.05912
0.69134     0.06694
0.66072     0.07394
0.62941     0.07989
0.59755     0.08482
0.56526     0.08887
0.53270     0.09215
0.50000     0.09469
0.46730     0.09650
0.43474     0.09759
0.40245     0.09796
0.37059     0.09762
0.33928     0.09659
0.30866     0.09486
0.27886     0.09245
0.25000     0.08938
0.22221     0.08569
0.19562     0.08146
0.17033     0.07671
0.14645     0.07146
0.12408     0.06579
0.10332     0.05973
0.08427     0.05341
0.06699     0.04680
0.05156     0.03990
0.03806     0.03315
0.02653     0.02676
0.01704     0.02019
0.00961     0.01410
0.00428     0.00864
0.00107     0.00435
0.00000     0.00000
0.00107     -0.00390
0.00428     -0.00688
0.00961     -0.00988
0.01704     -0.01304
0.02653     -0.01612
0.03806     -0.01866
0.05156     -0.02117
0.06699     -0.02344
0.08427     -0.02556
0.10332     -0.02747
0.12408     -0.02919
0.14645     -0.03074
0.17033     -0.03212
0.19562     -0.03332
0.22221     -0.03436
0.25000     -0.03522
0.27886     -0.03591
0.30866     -0.03642
0.33928     -0.03676
0.37059     -0.03693
0.40245     -0.03691
0.43474     -0.03669
0.46730     -0.03630
0.50000     -0.03571
0.53270     -0.03489
0.56526     -0.03387
0.59755     -0.03264
0.62941     -0.03112
0.66072     -0.02931
0.69134     -0.02726
0.72114     -0.02500
0.75000     -0.02244
0.77779     -0.01968
0.80438     -0.01681
0.82967     -0.01372
0.85355     -0.01060
0.87592     -0.00763
0.89668     -0.00499
0.91573     -0.00291
0.93301     -0.00141
0.94844     -0.00040
0.96194     0.00016
0.97347     0.00031
0.98296     0.00030
0.99039     0.00014
0.99572     -0.00007
0.99893     -0.00005
1.00000     0.00000
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Selig format dat file

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Polars for AH 79-K-135/20 B (ah79k135-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ah79k135-il50,000924 at α=10.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ah79k135-il50,000524.3 at α=10°Mach=0 Ncrit=5Xfoil predictionDetails
   ah79k135-il100,000948 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ah79k135-il100,000546.3 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   ah79k135-il200,000978.9 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ah79k135-il200,000574.4 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ah79k135-il500,0009104.3 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ah79k135-il500,000595 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ah79k135-il1,000,0009122.7 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ah79k135-il1,000,0005111.7 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
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