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AH 79-K-132/20 (ah79k132-il)

AH 79-K-132/20 - Althaus AH 79-K-132/20 airfoil for use with flaps (K)


Airfoil ah79k132-il
Details Dat file Parser  
(ah79k132-il) AH 79-K-132/20
Althaus AH 79-K-132/20 airfoil for use with flaps (K)
Max thickness 13.2% at 40.2% chord.
Max camber 3.7% at 40.2% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AH 79-K-132/20
1.00000     0.00000
0.99893     0.00041
0.99572     0.00152
0.99039     0.00300
0.98296     0.00475
0.97347     0.00679
0.96194     0.00906
0.94844     0.01156
0.93301     0.01434
0.91573     0.01732
0.89668     0.02057
0.87592     0.02389
0.85355     0.02764
0.82967     0.03187
0.80438     0.03709
0.77779     0.04463
0.75000     0.05320
0.72114     0.06175
0.69134     0.07007
0.66072     0.07741
0.62941     0.08370
0.59755     0.08887
0.56526     0.09316
0.53270     0.09663
0.50000     0.09931
0.46730     0.10124
0.43474     0.10240
0.40245     0.10280
0.37059     0.10245
0.33928     0.10136
0.30866     0.09953
0.27886     0.09698
0.25000     0.09372
0.22221     0.08982
0.19562     0.08533
0.17033     0.08029
0.14645     0.07472
0.12408     0.06871
0.10332     0.06231
0.08427     0.05560
0.06699     0.04868
0.05156     0.04132
0.03806     0.03424
0.02653     0.02755
0.01704     0.02085
0.00961     0.01435
0.00428     0.00851
0.00107     0.00363
0.00000     0.00000
0.00107     -0.00344
0.00428     -0.00698
0.00961     -0.01023
0.01704     -0.01339
0.02653     -0.01607
0.03806     -0.01827
0.05156     -0.02009
0.06699     -0.02139
0.08427     -0.02269
0.10332     -0.02384
0.12408     -0.02478
0.14645     -0.02561
0.17033     -0.02632
0.19562     -0.02695
0.22221     -0.02748
0.25000     -0.02795
0.27886     -0.02832
0.30866     -0.02864
0.33928     -0.02889
0.37059     -0.02908
0.40245     -0.02920
0.43474     -0.02924
0.46730     -0.02915
0.50000     -0.02889
0.53270     -0.02843
0.56526     -0.02778
0.59755     -0.02692
0.62941     -0.02583
0.66072     -0.02456
0.69134     -0.02302
0.72114     -0.02134
0.75000     -0.01933
0.77779     -0.01704
0.80438     -0.01467
0.82967     -0.01177
0.85355     -0.00886
0.87592     -0.00602
0.89668     -0.00347
0.91573     -0.00159
0.93301     -0.00026
0.94844     0.00055
0.96194     0.00090
0.97347     0.00083
0.98296     0.00063
0.99039     0.00023
0.99572     -0.00015
0.99893     -0.00010
1.00000     0.00000
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Polars for AH 79-K-132/20 (ah79k132-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ah79k132-il50,000921.8 at α=11.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ah79k132-il50,000522.4 at α=10.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ah79k132-il100,000947.8 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ah79k132-il100,000545.2 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ah79k132-il200,000979.2 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ah79k132-il200,000578.4 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ah79k132-il500,0009115 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ah79k132-il500,0005100 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ah79k132-il1,000,0009130.6 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ah79k132-il1,000,0005116.7 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
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