Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

AH 81-K-144/17 (ah81k144-il)

AH 81-K-144/17 - Althaus AH 81-K-144/17 airfoil for use with flaps (K)


Airfoil ah81k144-il
Details Dat file Parser  
(ah81k144-il) AH 81-K-144/17
Althaus AH 81-K-144/17 airfoil for use with flaps (K)
Max thickness 14.5% at 40.2% chord.
Max camber 4.2% at 46.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AH 81-K-144/17
1.00000     0.00000
0.99893     0.00113
0.99572     0.00180
0.99039     0.00287
0.98296     0.00424
0.97347     0.00609
0.96194     0.00840
0.94844     0.01116
0.93301     0.01440
0.91573     0.01812
0.89668     0.02229
0.87592     0.02684
0.85355     0.03177
0.82967     0.03731
0.80438     0.04378
0.77779     0.05133
0.75000     0.05981
0.72114     0.06882
0.69134     0.07789
0.66072     0.08649
0.62941     0.09415
0.59755     0.10055
0.56526     0.10562
0.53270     0.10944
0.50000     0.11212
0.46730     0.11376
0.43474     0.11444
0.40245     0.11421
0.37059     0.11311
0.33928     0.11119
0.30866     0.10846
0.27886     0.10498
0.25000     0.10080
0.22221     0.09598
0.19562     0.09057
0.17033     0.08464
0.14645     0.07824
0.12408     0.07149
0.10332     0.06447
0.08427     0.05728
0.06699     0.05001
0.05156     0.04276
0.03806     0.03563
0.02653     0.02872
0.01704     0.02212
0.00961     0.01601
0.00428     0.01033
0.00107     0.00505
0.00000     0.00037
0.00107     -0.00368
0.00428     -0.00717
0.00961     -0.01044
0.01704     -0.01368
0.02653     -0.01673
0.03806     -0.01948
0.05156     -0.02194
0.06699     -0.02411
0.08427     -0.02596
0.10332     -0.02749
0.12408     -0.02872
0.14645     -0.02968
0.17033     -0.03043
0.19562     -0.03099
0.22221     -0.03136
0.25000     -0.03156
0.27886     -0.03160
0.30866     -0.03150
0.33928     -0.03127
0.37059     -0.03091
0.40245     -0.03042
0.43474     -0.02979
0.46730     -0.02903
0.50000     -0.02813
0.53270     -0.02712
0.56526     -0.02599
0.59755     -0.02474
0.62941     -0.02336
0.66072     -0.02185
0.69134     -0.02018
0.72114     -0.01829
0.75000     -0.01612
0.77779     -0.01365
0.80438     -0.01092
0.82967     -0.00815
0.85355     -0.00563
0.87592     -0.00356
0.89668     -0.00201
0.91573     -0.00091
0.93301     -0.00022
0.94844     0.00012
0.96194     0.00017
0.97347     0.00001
0.98296     -0.00025
0.99039     -0.00059
0.99572     -0.00078
0.99893     -0.00087
1.00000     0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

EPPLER 582 AIRFOILPreviewDetails
EPPLER 585 AIRFOILPreviewDetails
EPPLER E662 AIRFOILPreviewDetails
EPPLER 433 AIRFOILPreviewDetails
FX 78-K-140/20PreviewDetails
FX 78-K-140 A/20PreviewDetails
NACA 2-H-15 AIRFOILPreviewDetails
EPPLER 668 AIRFOILPreviewDetails
NASA/LANGLEY NLF(1)-0215F AIRFOILPreviewDetails
EPPLER 431 AIRFOILPreviewDetails

Polars for AH 81-K-144/17 (ah81k144-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ah81k144-il50,000917.8 at α=13.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ah81k144-il50,000516.6 at α=12°Mach=0 Ncrit=5Xfoil predictionDetails
   ah81k144-il100,000929.8 at α=10.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ah81k144-il100,000530.5 at α=10°Mach=0 Ncrit=5Xfoil predictionDetails
   ah81k144-il200,000962.5 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ah81k144-il200,000567.4 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ah81k144-il500,0009129.4 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ah81k144-il500,0005117.3 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ah81k144-il1,000,0009156.1 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   ah81k144-il1,000,0005145.3 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit