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-140 (fx76mp140-il)

FX 76-MP-140 - Wortmann FX 76-MP-140 airfoil


Airfoil fx76mp140-il
Details Dat file Parser  
(fx76mp140-il) FX 76-MP-140
Wortmann FX 76-MP-140 airfoil
Max thickness 14.1% at 33.9% chord.
Max camber 7.1% at 46.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
FX 76-MP-140
1.00000     0.00000
0.99893     0.00145
0.99572     0.00293
0.99039     0.00509
0.98296     0.00787
0.97347     0.01118
0.96194     0.01496
0.94844     0.01936
0.93301     0.02433
0.91573     0.02995
0.89668     0.03617
0.87592     0.04303
0.85355     0.05048
0.82967     0.05851
0.80438     0.06708
0.77779     0.07613
0.75000     0.08541
0.72114     0.09466
0.69134     0.10341
0.66072     0.11139
0.62941     0.11842
0.59755     0.12451
0.56526     0.12952
0.53270     0.13352
0.50000     0.13652
0.46730     0.13862
0.43474     0.13977
0.40245     0.14003
0.37059     0.13935
0.33928     0.13779
0.30866     0.13531
0.27886     0.13200
0.25000     0.12779
0.22221     0.12277
0.19562     0.11695
0.17033     0.11043
0.14645     0.10324
0.12408     0.09557
0.10332     0.08734
0.08427     0.07869
0.06699     0.06946
0.05156     0.05986
0.03806     0.04998
0.02653     0.04044
0.01704     0.03121
0.00961     0.02273
0.00428     0.01459
0.00107     0.00750
0.00000     0.00000
0.00107     -0.00489
0.00428     -0.00938
0.00961     -0.01359
0.01704     -0.01688
0.02653     -0.01936
0.03806     -0.02085
0.05156     -0.02163
0.06699     -0.02171
0.08427     -0.02131
0.10332     -0.02043
0.12408     -0.01916
0.14645     -0.01755
0.17033     -0.01573
0.19562     -0.01376
0.22221     -0.01169
0.25000     -0.00958
0.27886     -0.00743
0.30866     -0.00534
0.33928     -0.00329
0.37059     -0.00136
0.40245     0.00048
0.43474     0.00218
0.46730     0.00381
0.50000     0.00532
0.53270     0.00675
0.56526     0.00806
0.59755     0.00933
0.62941     0.01051
0.66072     0.01171
0.69134     0.01287
0.72114     0.01404
0.75000     0.01510
0.77779     0.01599
0.80438     0.01651
0.82967     0.01668
0.85355     0.01639
0.87592     0.01572
0.89668     0.01461
0.91573     0.01319
0.93301     0.01147
0.94844     0.00959
0.96194     0.00755
0.97347     0.00549
0.98296     0.00349
0.99039     0.00171
0.99572     0.00032
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

USA 98 AIRFOILPreviewDetails
GOE 592 AIRFOILPreviewDetails
MH 113 14.62%PreviewDetails
FX 74-CL6-140PreviewDetails
GOE 366 AIRFOILPreviewDetails
WORTMANN FX 63-137 AIRFOILPreviewDetails
DAE-11 AIRFOILPreviewDetails
GOE 227 (MVA H.37) AIRFOILPreviewDetails
WORTMANN FX 72-MS-150A AIRFOILPreviewDetails
MH 114 13.02%PreviewDetails

Polars for FX 76-MP-140 (fx76mp140-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   fx76mp140-il50,00095.9 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   fx76mp140-il50,000514.1 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   fx76mp140-il100,000937.8 at α=12°Mach=0 Ncrit=9Xfoil predictionDetails
   fx76mp140-il100,000537.3 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
   fx76mp140-il200,000978.1 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   fx76mp140-il200,000578.3 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   fx76mp140-il500,0009138.2 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   fx76mp140-il500,0005131.5 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   fx76mp140-il1,000,0009181.6 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   fx76mp140-il1,000,0005153.4 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit