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AH 63-K-127/24 (ah63k127-il)

AH 63-K-127/24 - Althaus AH 63-K-127/24 airfoil for use with flaps (K)


Airfoil ah63k127-il
Details Dat file Parser  
(ah63k127-il) AH 63-K-127/24
Althaus AH 63-K-127/24 airfoil for use with flaps (K)
Max thickness 12.7% at 40.2% chord.
Max camber 3.8% at 43.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AH 63-K-127/24
1.00000     0.00000
0.99893     0.00080
0.99572     0.00180
0.99039     0.00311
0.98296     0.00489
0.97347     0.00709
0.96194     0.00956
0.94844     0.01222
0.93301     0.01521
0.91573     0.01865
0.89668     0.02254
0.87592     0.02667
0.85355     0.03085
0.82967     0.03477
0.80438     0.03919
0.77779     0.04532
0.75000     0.05330
0.72114     0.06237
0.69134     0.07088
0.66072     0.07810
0.62941     0.08418
0.59755     0.08913
0.56526     0.09314
0.53270     0.09631
0.50000     0.09866
0.46730     0.10021
0.43474     0.10098
0.40245     0.10096
0.37059     0.10010
0.33928     0.09839
0.30866     0.09587
0.27886     0.09262
0.25000     0.08874
0.22221     0.08428
0.19562     0.07934
0.17033     0.07405
0.14645     0.06848
0.12408     0.06273
0.10332     0.05685
0.08427     0.05091
0.06699     0.04490
0.05156     0.03876
0.03806     0.03253
0.02653     0.02631
0.01704     0.02021
0.00961     0.01430
0.00428     0.00879
0.00107     0.00394
0.00000     0.00000
0.00107     -0.00310
0.00428     -0.00565
0.00961     -0.00795
0.01704     -0.01021
0.02653     -0.01245
0.03806     -0.01459
0.05156     -0.01655
0.06699     -0.01830
0.08427     -0.01986
0.10332     -0.02125
0.12408     -0.02246
0.14645     -0.02347
0.17033     -0.02426
0.19562     -0.02485
0.22221     -0.02527
0.25000     -0.02559
0.27886     -0.02585
0.30866     -0.02608
0.33928     -0.02626
0.37059     -0.02630
0.40245     -0.02611
0.43474     -0.02568
0.46730     -0.02508
0.50000     -0.02432
0.53270     -0.02335
0.56526     -0.02217
0.59755     -0.02087
0.62941     -0.01936
0.66072     -0.01756
0.69134     -0.01539
0.72114     -0.01298
0.75000     -0.01050
0.77779     -0.00795
0.80438     -0.00540
0.82967     -0.00292
0.85355     -0.00071
0.87592     0.00098
0.89668     0.00208
0.91573     0.00266
0.93301     0.00285
0.94844     0.00272
0.96194     0.00228
0.97347     0.00174
0.98296     0.00122
0.99039     0.00077
0.99572     0.00030
0.99893     0.00010
1.00000     0.00000
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Polars for AH 63-K-127/24 (ah63k127-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ah63k127-il50,000925.4 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   ah63k127-il50,000523 at α=10°Mach=0 Ncrit=5Xfoil predictionDetails
   ah63k127-il100,000943.4 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   ah63k127-il100,000544.8 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ah63k127-il200,000983.2 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ah63k127-il200,000581.8 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ah63k127-il500,0009127.5 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   ah63k127-il500,0005115.4 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ah63k127-il1,000,0009152.3 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ah63k127-il1,000,0005137.8 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
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