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AH 88-K-136/16 (ah88k136-il)

AH 88-K-136/16 - Althaus AH 88-K-136/16 airfoil for use with flaps (K)


Airfoil ah88k136-il
Details Dat file Parser  
(ah88k136-il) AH 88-K-136/16
Althaus AH 88-K-136/16 airfoil for use with flaps (K)
Max thickness 13.5% at 44.9% chord.
Max camber 3% at 41.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AH 88-K-136/16
1.00058  -0.00010
0.99941   0.00017
0.99748   0.00067
0.99421   0.00148
0.98937   0.00257
0.98269   0.00388
0.97397   0.00534
0.96317   0.00692
0.95017   0.00856
0.93496   0.01023
0.91774   0.01197
0.89888   0.01386
0.87906   0.01607
0.85931   0.01884
0.84280   0.02030
0.82513   0.02687
0.81002   0.03181
0.79538   0.03714
0.78054   0.04277
0.76473   0.04856
0.74747   0.05445
0.72849   0.06039
0.70758   0.06630
0.68450   0.07208
0.65904   0.07762
0.63096   0.08278
0.60012   0.08740
0.56656   0.09136
0.53060   0.09452
0.49278   0.09681
0.45377   0.09818
0.41428   0.09857
0.37505   0.09798
0.33680   0.09644
0.30021   0.09400
0.26577   0.09077
0.23377   0.08687
0.20429   0.08242
0.17736   0.07755
0.15294   0.07237
0.13095   0.06700
0.11128   0.06152
0.09379   0.05602
0.07833   0.05058
0.06473   0.04526
0.05285   0.04010
0.04251   0.03515
0.03357   0.03044
0.02589   0.02600
0.01937   0.02183
0.01395   0.01797
0.00957   0.01443
0.00619   0.01122
0.00377   0.00838
0.00218   0.00591
0.00128   0.00384
0.00088   0.00217
0.00080   0.00092
0.00084   0.00009
0.00090  -0.00033
0.00092  -0.00042
0.00098  -0.00074
0.00114  -0.00136
0.00149  -0.00229
0.00214  -0.00353
0.00328  -0.00505
0.00511  -0.00684
0.00791  -0.00888
0.01200  -0.01111
0.01774  -0.01348
0.02553  -0.01591
0.03575  -0.01830
0.04860  -0.02054
0.06404  -0.02258
0.08188  -0.02439
0.10182  -0.02598
0.12351  -0.02738
0.14657  -0.02861
0.17069  -0.02973
0.19568  -0.03078
0.22144  -0.03178
0.24793  -0.03274
0.27509  -0.03365
0.30288  -0.03449
0.33123  -0.03525
0.36007  -0.03591
0.38932  -0.03646
0.41890  -0.03688
0.44872  -0.03718
0.47867  -0.03733
0.50866  -0.03735
0.53859  -0.03722
0.56836  -0.03694
0.59787  -0.03652
0.62702  -0.03596
0.65569  -0.03525
0.68379  -0.03440
0.71120  -0.03341
0.73782  -0.03227
0.76351  -0.03096
0.78806  -0.02945
0.81126  -0.02774
0.83291  -0.02579
0.85287  -0.02364
0.87109  -0.02130
0.88762  -0.01886
0.90260  -0.01638
0.91624  -0.01394
0.92876  -0.01163
0.94032  -0.00949
0.95099  -0.00756
0.96080  -0.00586
0.96977  -0.00441
0.97798  -0.00325
0.98534  -0.00237
0.99142  -0.00167
0.99581  -0.00105
0.99856  -0.00054
1.00008  -0.00021
1.00058  -0.00010
Dat file parser warnings
  • Line 2 - X value too large but included: 1.00058 -0.00010
  • Line 120 - X value too large but included: 1.00008 -0.00021
  • Line 121 - X value too large but included: 1.00058 -0.00010
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Polars for AH 88-K-136/16 (ah88k136-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ah88k136-il50,000921.1 at α=10.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ah88k136-il50,000521.8 at α=10°Mach=0 Ncrit=5Xfoil predictionDetails
   ah88k136-il100,000940.4 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ah88k136-il100,000538.7 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   ah88k136-il200,000973.3 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ah88k136-il200,000572.3 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   ah88k136-il500,0009113.3 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ah88k136-il500,000587.1 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ah88k136-il1,000,0009113.6 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   ah88k136-il1,000,000595.7 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
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