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AH 93-156 (ah93156-il)

AH 93-156 - Althaus AH 93-156 airfoil


Airfoil ah93156-il
Details Dat file Parser  
(ah93156-il) AH 93-156
Althaus AH 93-156 airfoil
Max thickness 15.7% at 39.5% chord.
Max camber 3.7% at 41.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AH 93-156
1.00000  -0.00197
0.99157   0.00025
0.97915   0.00318
0.96383   0.00651
0.94756   0.01005
0.92961   0.01406
0.91066   0.01849
0.89176   0.02317
0.87275   0.02810
0.85372   0.03325
0.83461   0.03858
0.81541   0.04407
0.79612   0.04968
0.77675   0.05534
0.75742   0.06097
0.73820   0.06649
0.71907   0.07188
0.70005   0.07707
0.68112   0.08202
0.66228   0.08669
0.64352   0.09103
0.62477   0.09501
0.60601   0.09862
0.58720   0.10186
0.56832   0.10474
0.54936   0.10726
0.53032   0.10943
0.51120   0.11126
0.49202   0.11276
0.47277   0.11394
0.45347   0.11482
0.43413   0.11540
0.41477   0.11568
0.39540   0.11568
0.37603   0.11540
0.35670   0.11482
0.33743   0.11394
0.31822   0.11274
0.29909   0.11122
0.28004   0.10935
0.26108   0.10712
0.24222   0.10452
0.22346   0.10155
0.20483   0.09818
0.18636   0.09441
0.16809   0.09022
0.15005   0.08559
0.13231   0.08050
0.11493   0.07492
0.09797   0.06883
0.08153   0.06221
0.06578   0.05506
0.05097   0.04742
0.03753   0.03949
0.02609   0.03166
0.01716   0.02450
0.01073   0.01837
0.00628   0.01327
0.00326   0.00898
0.00129   0.00526
0.00019   0.00196
0.00006  -0.00113
0.00086  -0.00422
0.00268  -0.00735
0.00561  -0.01038
0.00979  -0.01333
0.01556  -0.01627
0.02354  -0.01927
0.03443  -0.02233
0.04846  -0.02529
0.06493  -0.02795
0.08286  -0.03022
0.10159  -0.03211
0.12077  -0.03369
0.14022  -0.03502
0.15985  -0.03615
0.17961  -0.03711
0.19946  -0.03792
0.21936  -0.03861
0.23932  -0.03919
0.25931  -0.03967
0.27933  -0.04006
0.29938  -0.04037
0.31945  -0.04061
0.33955  -0.04078
0.35967  -0.04089
0.37980  -0.04095
0.39994  -0.04095
0.42009  -0.04092
0.44024  -0.04083
0.46039  -0.04070
0.48054  -0.04053
0.50066  -0.04030
0.52077  -0.04002
0.54085  -0.03968
0.56091  -0.03927
0.58094  -0.03878
0.60094  -0.03820
0.62090  -0.03753
0.64081  -0.03675
0.66067  -0.03585
0.68048  -0.03481
0.70021  -0.03362
0.71987  -0.03226
0.73941  -0.03071
0.75882  -0.02893
0.77805  -0.02690
0.79710  -0.02456
0.81603  -0.02187
0.83496  -0.01880
0.85409  -0.01538
0.87330  -0.01180
0.89212  -0.00847
0.91039  -0.00570
0.92825  -0.00360
0.94574  -0.00226
0.96269  -0.00172
0.97854  -0.00183
0.99127  -0.00201
1.00000  -0.00197
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Polars for AH 93-156 (ah93156-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ah93156-il50,00094.8 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ah93156-il50,000515.6 at α=12°Mach=0 Ncrit=5Xfoil predictionDetails
   ah93156-il100,000939 at α=11.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ah93156-il100,000535.5 at α=10.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ah93156-il200,000972.1 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   ah93156-il200,000564.7 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ah93156-il500,0009103.1 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ah93156-il500,000594.1 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ah93156-il1,000,0009125 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   ah93156-il1,000,0005114.9 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
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