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

AH 83-150 Q (ah83150q-il)

AH 83-150 Q - Althaus AH 83-150 Q airfoil


Airfoil ah83150q-il
Details Dat file Parser  
(ah83150q-il) AH 83-150 Q
Althaus AH 83-150 Q airfoil
Max thickness 15% at 40.2% chord.
Max camber 4.1% at 37.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AH 83-150 Q
1.00000     0.00000
0.99893     0.00029
0.99572     0.00060
0.99039     0.00137
0.98296     0.00251
0.97347     0.00410
0.96194     0.00617
0.94844     0.00872
0.93301     0.01175
0.91573     0.01529
0.89668     0.01935
0.87592     0.02393
0.85355     0.02901
0.82967     0.03458
0.80438     0.04067
0.77779     0.04728
0.75000     0.05434
0.72114     0.06176
0.69134     0.06946
0.66072     0.07733
0.62941     0.08517
0.59755     0.09264
0.56526     0.09934
0.53270     0.10500
0.50000     0.10950
0.46730     0.11282
0.43474     0.11503
0.40245     0.11616
0.37059     0.11633
0.33928     0.11560
0.30866     0.11400
0.27886     0.11157
0.25000     0.10836
0.22221     0.10440
0.19562     0.09973
0.17033     0.09440
0.14645     0.08849
0.12408     0.08208
0.10332     0.07529
0.08427     0.06819
0.06699     0.06071
0.05156     0.05289
0.03806     0.04486
0.02653     0.03684
0.01704     0.02896
0.00961     0.02118
0.00428     0.01327
0.00107     0.00584
0.00000     0.00000
0.00107     -0.00394
0.00428     -0.00642
0.00961     -0.00862
0.01704     -0.01106
0.02653     -0.01342
0.03806     -0.01569
0.05156     -0.01786
0.06699     -0.01991
0.08427     -0.02184
0.10332     -0.02361
0.12408     -0.02523
0.14645     -0.02674
0.17033     -0.02810
0.19562     -0.02929
0.22221     -0.03036
0.25000     -0.03132
0.27886     -0.03215
0.30866     -0.03284
0.33928     -0.03335
0.37059     -0.03368
0.40245     -0.03387
0.43474     -0.03393
0.46730     -0.03386
0.50000     -0.03361
0.53270     -0.03315
0.56526     -0.03250
0.59755     -0.03163
0.62941     -0.03046
0.66072     -0.02890
0.69134     -0.02686
0.72114     -0.02428
0.75000     -0.02106
0.77779     -0.01718
0.80438     -0.01287
0.82967     -0.00866
0.85355     -0.00500
0.87592     -0.00218
0.89668     -0.00027
0.91573     0.00086
0.93301     0.00139
0.94844     0.00153
0.96194     0.00142
0.97347     0.00109
0.98296     0.00071
0.99039     0.00042
0.99572     0.00026
0.99893     0.00016
1.00000     0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

FX 84-W-150PreviewDetails
NACA 2-H-15 AIRFOILPreviewDetails
NASA/LANGLEY NLF(1)-0215F AIRFOILPreviewDetails
EPPLER 431 AIRFOILPreviewDetails
HORSTMANN AND QUAST HQ-17/14.38PreviewDetails
EPPLER 582 AIRFOILPreviewDetails
NACA 6-H-15 AIRFOILPreviewDetails
EPPLER 585 AIRFOILPreviewDetails
FX 78-K-150/20PreviewDetails
AH 94-156PreviewDetails

Polars for AH 83-150 Q (ah83150q-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ah83150q-il50,00096.7 at α=11.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ah83150q-il50,000515.9 at α=12°Mach=0 Ncrit=5Xfoil predictionDetails
   ah83150q-il100,000939.6 at α=11°Mach=0 Ncrit=9Xfoil predictionDetails
   ah83150q-il100,000535.4 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ah83150q-il200,000973.9 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   ah83150q-il200,000571.7 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ah83150q-il500,0009109.7 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ah83150q-il500,0005102.2 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ah83150q-il1,000,0009134.7 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ah83150q-il1,000,0005122.8 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit