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

AUGUST 160 (august160-il)

AUGUST 160 - AUGUST 160 airfoil


Airfoil august160-il
Details Dat file Parser  
(august160-il) AUGUST 160
AUGUST 160 airfoil
Max thickness 16% at 25% chord.
Max camber 5.4% at 25% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AUGUST 160
1.00000     0.00000
0.99893     0.00111
0.99572     0.00175
0.99039     0.00272
0.98296     0.00406
0.97347     0.00578
0.96194     0.00788
0.94844     0.01033
0.93301     0.01318
0.91573     0.01634
0.89668     0.01986
0.87592     0.02365
0.85355     0.02773
0.82967     0.03214
0.80438     0.03688
0.77779     0.04193
0.75000     0.04732
0.72114     0.05309
0.69134     0.05913
0.66072     0.06546
0.62941     0.07195
0.59755     0.07869
0.56526     0.08545
0.53270     0.09232
0.50000     0.09903
0.46730     0.10571
0.43474     0.11203
0.40245     0.11795
0.37059     0.12317
0.33928     0.12765
0.30866     0.13107
0.27886     0.13338
0.25000     0.13406
0.22221     0.13301
0.19562     0.12969
0.17033     0.12467
0.14645     0.11787
0.12408     0.11026
0.10332     0.10130
0.08427     0.09207
0.06699     0.08178
0.05156     0.07169
0.03806     0.06078
0.02653     0.05061
0.01704     0.04100
0.00961     0.03150
0.00428     0.02200
0.00107     0.01311
0.00000     0.00000
0.00107     -0.00360
0.00428     -0.00741
0.00961     -0.01000
0.01704     -0.01250
0.02653     -0.01500
0.03806     -0.01712
0.05156     -0.01900
0.06699     -0.02075
0.08427     -0.02241
0.10332     -0.02320
0.12408     -0.02435
0.14645     -0.02484
0.17033     -0.02562
0.19562     -0.02584
0.22221     -0.02629
0.25000     -0.02632
0.27886     -0.02650
0.30866     -0.02638
0.33928     -0.02633
0.37059     -0.02606
0.40245     -0.02582
0.43474     -0.02538
0.46730     -0.02498
0.50000     -0.02439
0.53270     -0.02385
0.56526     -0.02312
0.59755     -0.02243
0.62941     -0.02158
0.66072     -0.02077
0.69134     -0.01977
0.72114     -0.01881
0.75000     -0.01768
0.77779     -0.01653
0.80438     -0.01521
0.82967     -0.01366
0.85355     -0.01200
0.87592     -0.01024
0.89668     -0.00844
0.91573     -0.00674
0.93301     -0.00517
0.94844     -0.00376
0.96194     -0.00261
0.97347     -0.00172
0.98296     -0.00113
0.99039     -0.00086
0.99572     -0.00082
0.99893     -0.00085
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 1210 AIRFOILPreviewDetails
Glenn Martin 4PreviewDetails
GOE 741 AIRFOILPreviewDetails
WORTMANN FX 77-W-153 AIRFOILPreviewDetails
FX 73-CL1-152PreviewDetails
GOE 627 AIRFOILPreviewDetails
STRAND AIRFOILPreviewDetails
GOE 647 AIRFOILPreviewDetails
GOE 711 AIRFOILPreviewDetails
GOE 624 AIRFOILPreviewDetails

Polars for AUGUST 160 (august160-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   august160-il50,00094.7 at α=-0.5°Mach=0 Ncrit=9Xfoil predictionDetails
   august160-il50,000517.3 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   august160-il100,000920.8 at α=0°Mach=0 Ncrit=9Xfoil predictionDetails
   august160-il100,000534.7 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   august160-il200,000942.5 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   august160-il200,000556.1 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   august160-il500,000982.1 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   august160-il500,000590.3 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   august160-il1,000,0009117.2 at α=11°Mach=0 Ncrit=9Xfoil predictionDetails
   august160-il1,000,0005120.2 at α=9.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit