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AH 88-K-130/20 (ah88k130-il)

AH 88-K-130/20 - Althaus AH 88-K-130/20 airfoil for use with flaps (K)


Airfoil ah88k130-il
Details Dat file Parser  
(ah88k130-il) AH 88-K-130/20
Althaus AH 88-K-130/20 airfoil for use with flaps (K)
Max thickness 13% at 43.5% chord.
Max camber 3.9% at 46.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AH 88-K-130/20
1.00000     0.00000
0.99893     0.00050
0.99572     0.00166
0.99039     0.00324
0.98296     0.00523
0.97347     0.00766
0.96194     0.01054
0.94844     0.01390
0.93301     0.01777
0.91573     0.02216
0.89668     0.02720
0.87592     0.03263
0.85355     0.03865
0.82967     0.04524
0.80438     0.05229
0.77779     0.05983
0.75000     0.06761
0.72114     0.07531
0.69134     0.08191
0.66072     0.08742
0.62941     0.09204
0.59755     0.09600
0.56526     0.09921
0.53270     0.10171
0.50000     0.10345
0.46730     0.10429
0.43474     0.10410
0.40245     0.10321
0.37059     0.10160
0.33928     0.09935
0.30866     0.09648
0.27886     0.09304
0.25000     0.08911
0.22221     0.08467
0.19562     0.07982
0.17033     0.07458
0.14645     0.06905
0.12408     0.06315
0.10332     0.05712
0.08427     0.05086
0.06699     0.04458
0.05156     0.03815
0.03806     0.03190
0.02653     0.02555
0.01704     0.01986
0.00961     0.01400
0.00428     0.00889
0.00107     0.00445
0.00000     0.00000
0.00107     -0.00252
0.00428     -0.00503
0.00961     -0.00747
0.01704     -0.00951
0.02653     -0.01138
0.03806     -0.01339
0.05156     -0.01494
0.06699     -0.01661
0.08427     -0.01803
0.10332     -0.01939
0.12408     -0.02058
0.14645     -0.02174
0.17033     -0.02271
0.19562     -0.02359
0.22221     -0.02436
0.25000     -0.02500
0.27886     -0.02548
0.30866     -0.02588
0.33928     -0.02612
0.37059     -0.02619
0.40245     -0.02614
0.43474     -0.02590
0.46730     -0.02549
0.50000     -0.02484
0.53270     -0.02393
0.56526     -0.02264
0.59755     -0.02120
0.62941     -0.01956
0.66072     -0.01782
0.69134     -0.01584
0.72114     -0.01374
0.75000     -0.01118
0.77779     -0.00793
0.80438     -0.00452
0.82967     -0.00162
0.85355     0.00073
0.87592     0.00246
0.89668     0.00390
0.91573     0.00429
0.93301     0.00450
0.94844     0.00435
0.96194     0.00389
0.97347     0.00323
0.98296     0.00245
0.99039     0.00165
0.99572     0.00095
0.99893     0.00032
1.00000     0.00000
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Polars for AH 88-K-130/20 (ah88k130-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ah88k130-il50,000923.2 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   ah88k130-il50,000523.9 at α=9.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ah88k130-il100,000942.5 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ah88k130-il100,000543 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ah88k130-il200,000980.4 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ah88k130-il200,000579 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ah88k130-il500,0009121.2 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ah88k130-il500,0005113.7 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ah88k130-il1,000,0009147.2 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   ah88k130-il1,000,0005136.2 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
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