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

FX 76-MP-160 (fx76mp160-il)

FX 76-MP-160 - Wortmann FX 76-MP-160 airfoil


Airfoil fx76mp160-il
Details Dat file Parser  
(fx76mp160-il) FX 76-MP-160
Wortmann FX 76-MP-160 airfoil
Max thickness 16.1% at 33.9% chord.
Max camber 6.1% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
FX 76-MP-160
1.00000     0.00000
0.99893     0.00126
0.99572     0.00284
0.99039     0.00493
0.98296     0.00762
0.97347     0.01090
0.96194     0.01462
0.94844     0.01904
0.93301     0.02392
0.91573     0.02958
0.89668     0.03567
0.87592     0.04257
0.85355     0.04984
0.82967     0.05790
0.80438     0.06626
0.77779     0.07531
0.75000     0.08442
0.72114     0.09364
0.69134     0.10221
0.66072     0.11007
0.62941     0.11686
0.59755     0.12285
0.56526     0.12768
0.53270     0.13172
0.50000     0.13464
0.46730     0.13698
0.43474     0.13827
0.40245     0.13892
0.37059     0.13850
0.33928     0.13751
0.30866     0.13544
0.27886     0.13282
0.25000     0.12910
0.22221     0.12486
0.19562     0.11955
0.17033     0.11375
0.14645     0.10687
0.12408     0.09954
0.10332     0.09127
0.08427     0.08273
0.06699     0.07347
0.05156     0.06412
0.03806     0.05415
0.02653     0.04442
0.01704     0.03439
0.00961     0.02498
0.00428     0.01589
0.00107     0.00796
0.00000     0.00000
0.00107     -0.00567
0.00428     -0.01129
0.00961     -0.01697
0.01704     -0.02124
0.02653     -0.02544
0.03806     -0.02819
0.05156     -0.03099
0.06699     -0.03249
0.08427     -0.03410
0.10332     -0.03444
0.12408     -0.03483
0.14645     -0.03407
0.17033     -0.03362
0.19562     -0.03214
0.22221     -0.03111
0.25000     -0.02919
0.27886     -0.02779
0.30866     -0.02557
0.33928     -0.02396
0.37059     -0.02164
0.40245     -0.01995
0.43474     -0.01761
0.46730     -0.01589
0.50000     -0.01350
0.53270     -0.01175
0.56526     -0.00932
0.59755     -0.00742
0.62941     -0.00482
0.66072     -0.00262
0.69134     0.00029
0.72114     0.00276
0.75000     0.00575
0.77779     0.00787
0.80438     0.01012
0.82967     0.01116
0.85355     0.01225
0.87592     0.01210
0.89668     0.01202
0.91573     0.01085
0.93301     0.00992
0.94844     0.00809
0.96194     0.00663
0.97347     0.00458
0.98296     0.00312
0.99039     0.00143
0.99572     0.00066
0.99893     0.00045
1.00000     0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

GOE 502 AIRFOILPreviewDetails
MH 112 AirfoilPreviewDetails
DOUGLAS LA203A AIRFOILPreviewDetails
GOE 498 AIRFOILPreviewDetails
AH 95-160PreviewDetails
LIEBECK LA5055 AIRFOILPreviewDetails
GOE 508 AIRFOILPreviewDetails
GOE 527 AIRFOILPreviewDetails
GOE 289 (MVA 289) AIRFOILPreviewDetails
Rhode St. Genese 36PreviewDetails

Polars for FX 76-MP-160 (fx76mp160-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx76mp160-il50,00095.3 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   fx76mp160-il50,000516.4 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx76mp160-il100,000944.4 at α=10.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx76mp160-il100,000540.1 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx76mp160-il200,000976.3 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   fx76mp160-il200,000572 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx76mp160-il500,0009120.9 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   fx76mp160-il500,0005109.3 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   fx76mp160-il1,000,0009152.5 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   fx76mp160-il1,000,0005110.6 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit