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AH 93-157 (ah93157-il)

AH 93-157 - Althaus AH 93-157 airfoil


Airfoil ah93157-il
Details Dat file Parser  
(ah93157-il) AH 93-157
Althaus AH 93-157 airfoil
Max thickness 15.7% at 39.6% chord.
Max camber 3.5% at 41.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AH 93-157
1.00000  -0.00221
0.99124   0.00018
0.97859   0.00326
0.96180   0.00711
0.94302   0.01149
0.92371   0.01612
0.90430   0.02092
0.88486   0.02584
0.86540   0.03089
0.84592   0.03606
0.82641   0.04134
0.80686   0.04672
0.78725   0.05218
0.76758   0.05769
0.74797   0.06318
0.72855   0.06856
0.70932   0.07374
0.69025   0.07869
0.67128   0.08336
0.65236   0.08773
0.63345   0.09179
0.61452   0.09553
0.59556   0.09894
0.57653   0.10204
0.55746   0.10480
0.53831   0.10725
0.51912   0.10938
0.49987   0.11120
0.48058   0.11271
0.46126   0.11391
0.44191   0.11479
0.42256   0.11538
0.40320   0.11565
0.38386   0.11561
0.36453   0.11525
0.34523   0.11458
0.32598   0.11358
0.30679   0.11226
0.28766   0.11059
0.26863   0.10858
0.24973   0.10621
0.23098   0.10347
0.21237   0.10033
0.19395   0.09679
0.17573   0.09283
0.15777   0.08842
0.14011   0.08356
0.12281   0.07823
0.10595   0.07241
0.08960   0.06612
0.07388   0.05934
0.05894   0.05207
0.04501   0.04440
0.03256   0.03656
0.02223   0.02906
0.01443   0.02244
0.00893   0.01688
0.00514   0.01223
0.00256   0.00824
0.00092   0.00470
0.00010   0.00147
0.00010  -0.00155
0.00094  -0.00462
0.00275  -0.00765
0.00557  -0.01058
0.00953  -0.01341
0.01491  -0.01621
0.02219  -0.01906
0.03205  -0.02197
0.04489  -0.02486
0.06042  -0.02753
0.07777  -0.02987
0.09618  -0.03185
0.11521  -0.03351
0.13463  -0.03491
0.15429  -0.03609
0.17413  -0.03710
0.19410  -0.03796
0.21414  -0.03869
0.23426  -0.03930
0.25442  -0.03981
0.27462  -0.04022
0.29486  -0.04055
0.31514  -0.04081
0.33544  -0.04099
0.35577  -0.04112
0.37612  -0.04118
0.39649  -0.04120
0.41687  -0.04117
0.43725  -0.04109
0.45762  -0.04097
0.47799  -0.04080
0.49834  -0.04058
0.51867  -0.04030
0.53897  -0.03996
0.55923  -0.03955
0.57946  -0.03906
0.59965  -0.03848
0.61979  -0.03781
0.63988  -0.03703
0.65991  -0.03613
0.67987  -0.03509
0.69974  -0.03389
0.71952  -0.03253
0.73917  -0.03097
0.75866  -0.02919
0.77795  -0.02715
0.79703  -0.02482
0.81595  -0.02213
0.83491  -0.01905
0.85411  -0.01562
0.87350  -0.01201
0.89232  -0.00868
0.91048  -0.00593
0.92814  -0.00385
0.94541  -0.00252
0.96226  -0.00196
0.97822  -0.00206
0.99105  -0.00225
1.00000  -0.00221
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Polars for AH 93-157 (ah93157-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ah93157-il50,00094.7 at α=11°Mach=0 Ncrit=9Xfoil predictionDetails
   ah93157-il50,000514.4 at α=12.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ah93157-il100,000940 at α=10.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ah93157-il100,000537.5 at α=9.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ah93157-il200,000974.9 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ah93157-il200,000566.2 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ah93157-il500,0009100.4 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ah93157-il500,000592 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   ah93157-il1,000,0009120.6 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ah93157-il1,000,0005112.2 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
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