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AH 94-156 (ah94156-il)

AH 94-156 - Althaus AH 94-156 airfoil


Airfoil ah94156-il
Details Dat file Parser  
(ah94156-il) AH 94-156
Althaus AH 94-156 airfoil
Max thickness 15.6% at 39.6% chord.
Max camber 3.6% at 41.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AH 94-156
1.00000   0.00037
0.99137   0.00186
0.97931   0.00426
0.96327   0.00776
0.94505   0.01180
0.92619   0.01617
0.90722   0.02073
0.88826   0.02547
0.86931   0.03036
0.85035   0.03542
0.83137   0.04062
0.81233   0.04595
0.79321   0.05138
0.77404   0.05684
0.75493   0.06226
0.73591   0.06758
0.71697   0.07276
0.69811   0.07775
0.67934   0.08251
0.66063   0.08700
0.64197   0.09118
0.62332   0.09502
0.60465   0.09851
0.58593   0.10164
0.56716   0.10442
0.54832   0.10686
0.52941   0.10895
0.51043   0.11071
0.49139   0.11216
0.47230   0.11329
0.45317   0.11413
0.43400   0.11467
0.41481   0.11493
0.39561   0.11490
0.37643   0.11460
0.35726   0.11400
0.33815   0.11311
0.31910   0.11191
0.30011   0.11040
0.28120   0.10854
0.26237   0.10634
0.24364   0.10378
0.22500   0.10084
0.20649   0.09753
0.18812   0.09381
0.16993   0.08969
0.15195   0.08513
0.13425   0.08012
0.11686   0.07463
0.09986   0.06863
0.08330   0.06208
0.06734   0.05501
0.05224   0.04747
0.03849   0.03962
0.02674   0.03185
0.01755   0.02471
0.01093   0.01857
0.00636   0.01345
0.00326   0.00912
0.00125   0.00536
0.00019   0.00199
0.00006  -0.00109
0.00100  -0.00417
0.00319  -0.00710
0.00661  -0.00975
0.01141  -0.01229
0.01806  -0.01492
0.02735  -0.01775
0.03996  -0.02076
0.05558  -0.02374
0.07305  -0.02643
0.09141  -0.02876
0.11023  -0.03075
0.12934  -0.03247
0.14864  -0.03395
0.16807  -0.03523
0.18759  -0.03635
0.20717  -0.03732
0.22681  -0.03816
0.24649  -0.03887
0.26620  -0.03947
0.28593  -0.03997
0.30569  -0.04038
0.32546  -0.04070
0.34524  -0.04093
0.36504  -0.04108
0.38484  -0.04115
0.40465  -0.04115
0.42446  -0.04107
0.44428  -0.04091
0.46409  -0.04069
0.48390  -0.04039
0.50371  -0.04001
0.52352  -0.03957
0.54331  -0.03904
0.56309  -0.03844
0.58286  -0.03775
0.60261  -0.03698
0.62234  -0.03611
0.64204  -0.03514
0.66170  -0.03407
0.68130  -0.03287
0.70084  -0.03154
0.72027  -0.03005
0.73953  -0.02837
0.75854  -0.02646
0.77719  -0.02423
0.79560  -0.02152
0.81419  -0.01827
0.83326  -0.01465
0.85241  -0.01102
0.87125  -0.00767
0.88977  -0.00474
0.90798  -0.00234
0.92591  -0.00058
0.94364   0.00045
0.96127   0.00075
0.97789   0.00062
0.99101   0.00045
1.00000   0.00037
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Polars for AH 94-156 (ah94156-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ah94156-il50,00096.3 at α=12.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ah94156-il50,000516.7 at α=13°Mach=0 Ncrit=5Xfoil predictionDetails
   ah94156-il100,000940.2 at α=11.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ah94156-il100,000536.3 at α=10°Mach=0 Ncrit=5Xfoil predictionDetails
   ah94156-il200,000972.8 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   ah94156-il200,000564.4 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ah94156-il500,0009103.2 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ah94156-il500,000595.2 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ah94156-il1,000,0009125.1 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   ah94156-il1,000,0005115.4 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
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