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AH 82-150 A (ah82150a-il)

AH 82-150 A - Althaus AH 82-150 A airfoil


Airfoil ah82150a-il
Details Dat file Parser  
(ah82150a-il) AH 82-150 A
Althaus AH 82-150 A airfoil
Max thickness 15% at 40.2% chord.
Max camber 3.3% at 43.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AH 82-150 A
1.00000     0.00000
0.99893     0.00046
0.99572     0.00150
0.99039     0.00298
0.98296     0.00487
0.97347     0.00714
0.96194     0.00984
0.94844     0.01300
0.93301     0.01666
0.91573     0.02083
0.89668     0.02549
0.87592     0.03065
0.85355     0.03628
0.82967     0.04234
0.80438     0.04876
0.77779     0.05550
0.75000     0.06246
0.72114     0.06950
0.69134     0.07643
0.66072     0.08304
0.62941     0.08914
0.59755     0.09450
0.56526     0.09901
0.53270     0.10258
0.50000     0.10523
0.46730     0.10695
0.43474     0.10778
0.40245     0.10779
0.37059     0.10704
0.33928     0.10556
0.30866     0.10337
0.27886     0.10045
0.25000     0.09682
0.22221     0.09249
0.19562     0.08751
0.17033     0.08196
0.14645     0.07590
0.12408     0.06943
0.10332     0.06262
0.08427     0.05558
0.06699     0.04843
0.05156     0.04126
0.03806     0.03409
0.02653     0.02698
0.01704     0.02016
0.00961     0.01397
0.00428     0.00861
0.00107     0.00406
0.00000     0.00000
0.00107     -0.00395
0.00428     -0.00790
0.00961     -0.01169
0.01704     -0.01511
0.02653     -0.01808
0.03806     -0.02078
0.05156     -0.02332
0.06699     -0.02572
0.08427     -0.02799
0.10332     -0.03011
0.12408     -0.03209
0.14645     -0.03389
0.17033     -0.03550
0.19562     -0.03692
0.22221     -0.03817
0.25000     -0.03924
0.27886     -0.04016
0.30866     -0.04093
0.33928     -0.04155
0.37059     -0.04199
0.40245     -0.04220
0.43474     -0.04216
0.46730     -0.04184
0.50000     -0.04122
0.53270     -0.04023
0.56526     -0.03880
0.59755     -0.03674
0.62941     -0.03384
0.66072     -0.03006
0.69134     -0.02562
0.72114     -0.02089
0.75000     -0.01624
0.77779     -0.01192
0.80438     -0.00808
0.82967     -0.00482
0.85355     -0.00217
0.87592     -0.00013
0.89668     0.00134
0.91573     0.00229
0.93301     0.00279
0.94844     0.00291
0.96194     0.00271
0.97347     0.00229
0.98296     0.00176
0.99039     0.00120
0.99572     0.00070
0.99893     0.00026
1.00000     0.00000
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Selig format dat file

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Polars for AH 82-150 A (ah82150a-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ah82150a-il50,000917.8 at α=13°Mach=0 Ncrit=9Xfoil predictionDetails
   ah82150a-il50,000520.2 at α=10.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ah82150a-il100,000942.5 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ah82150a-il100,000541.9 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ah82150a-il200,000972.8 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   ah82150a-il200,000573.4 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ah82150a-il500,0009108.7 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   ah82150a-il500,0005107.4 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ah82150a-il1,000,0009137.6 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   ah82150a-il1,000,0005129.9 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
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