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AH 93-K-132/15 (ah93k132-il)

AH 93-K-132/15 - Althaus AH 93-K-132/15 airfoil for use with flaps (K)


Airfoil ah93k132-il
Details Dat file Parser  
(ah93k132-il) AH 93-K-132/15
Althaus AH 93-K-132/15 airfoil for use with flaps (K)
Max thickness 13.2% at 41.2% chord.
Max camber 3.5% at 41.2% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AH 93-K-132/15
1.00000   0.00071
0.97897   0.00192
0.96313   0.00352
0.94521   0.00573
0.92646   0.00832
0.90745   0.01114
0.88859   0.01406
0.87068   0.01711
0.85388   0.02083
0.83732   0.02571
0.82000   0.03169
0.80183   0.03818
0.78351   0.04477
0.76535   0.05131
0.74750   0.05749
0.72983   0.06316
0.71216   0.06827
0.69434   0.07285
0.67628   0.07696
0.65800   0.08065
0.63952   0.08398
0.62089   0.08696
0.60214   0.08962
0.58331   0.09198
0.56440   0.09406
0.54543   0.09586
0.52641   0.09738
0.50734   0.09866
0.48823   0.09969
0.46911   0.10048
0.44998   0.10102
0.43087   0.10131
0.41175   0.10135
0.39264   0.10114
0.37355   0.10067
0.35448   0.09994
0.33543   0.09894
0.31640   0.09767
0.29740   0.09613
0.27845   0.09432
0.25955   0.09223
0.24073   0.08985
0.22200   0.08715
0.20337   0.08414
0.18485   0.08078
0.16647   0.07706
0.14825   0.07297
0.13024   0.06848
0.11249   0.06356
0.09507   0.05818
0.07809   0.05231
0.06178   0.04597
0.04656   0.03919
0.03307   0.03220
0.02212   0.02548
0.01404   0.01951
0.00841   0.01444
0.00455   0.01014
0.00199   0.00639
0.00049   0.00300
0.00000   0.00003
0.00068  -0.00288
0.00291  -0.00542
0.00645  -0.00763
0.01135  -0.00974
0.01820  -0.01194
0.02792  -0.01432
0.04134  -0.01680
0.05781  -0.01918
0.07581  -0.02125
0.09454  -0.02300
0.11356  -0.02444
0.13267  -0.02565
0.15185  -0.02664
0.17117  -0.02745
0.19062  -0.02812
0.21011  -0.02869
0.22964  -0.02915
0.24925  -0.02955
0.26886  -0.02989
0.28845  -0.03016
0.30810  -0.03038
0.32779  -0.03057
0.34746  -0.03073
0.36708  -0.03086
0.38671  -0.03091
0.40639  -0.03093
0.42611  -0.03093
0.44581  -0.03094
0.46552  -0.03096
0.48520  -0.03098
0.50483  -0.03095
0.52449  -0.03087
0.55644  -0.03070
0.57639  -0.03050
0.59632  -0.03025
0.61624  -0.02993
0.63616  -0.02954
0.65606  -0.02909
0.67595  -0.02856
0.69582  -0.02796
0.71566  -0.02726
0.73546  -0.02646
0.75521  -0.02555
0.77490  -0.02452
0.79452  -0.02337
0.81399  -0.02213
0.83331  -0.02078
0.85241  -0.01933
0.87006  -0.01788
0.88577  -0.01646
0.90023  -0.01502
0.91399  -0.01348
0.92753  -0.01177
0.94171  -0.00964
0.95644  -0.00692
0.96941  -0.00398
0.98074  -0.00187
0.99147  -0.00051
1.00000  -0.00014
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Polars for AH 93-K-132/15 (ah93k132-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ah93k132-il50,000925.8 at α=10.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ah93k132-il50,000522.8 at α=10.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ah93k132-il100,000942.5 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ah93k132-il100,000540 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ah93k132-il200,000973.4 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ah93k132-il200,000571.7 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ah93k132-il500,0009114.6 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   ah93k132-il500,000599.1 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   ah93k132-il1,000,0009134.6 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ah93k132-il1,000,0005103.4 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
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