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

E475 (15.01%) (e475-il)

E475 (15.01%) - Eppler E475 aerobatic aircraft airfoil


Airfoil e475-il
Details Dat file Parser  
(e475-il) E475 (15.01%)
Eppler E475 aerobatic aircraft airfoil
Max thickness 15% at 21.7% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
E475  (15.01%)               
   1.00000  0.00000
   0.99608  0.00033
   0.98478  0.00168
   0.96708  0.00447
   0.94380  0.00854
   0.91560  0.01369
   0.88326  0.01958
   0.84723  0.02542
   0.80734  0.03083
   0.76375  0.03605
   0.71704  0.04120
   0.66781  0.04624
   0.61667  0.05115
   0.56426  0.05586
   0.51124  0.06027
   0.45826  0.06432
   0.40598  0.06789
   0.35504  0.07088
   0.30609  0.07317
   0.25973  0.07460
   0.21656  0.07500
   0.17717  0.07407
   0.14181  0.07131
   0.11033  0.06654
   0.08267  0.05991
   0.05881  0.05165
   0.03879  0.04211
   0.02270  0.03167
   0.01065  0.02076
   0.00283  0.00992
   0.00000  0.00000
   0.00283 -0.00992
   0.01065 -0.02076
   0.02270 -0.03167
   0.03879 -0.04211
   0.05881 -0.05165
   0.08267 -0.05991
   0.11033 -0.06654
   0.14181 -0.07131
   0.17717 -0.07407
   0.21656 -0.07500
   0.25973 -0.07460
   0.30609 -0.07317
   0.35504 -0.07088
   0.40598 -0.06789
   0.45826 -0.06432
   0.51124 -0.06027
   0.56426 -0.05586
   0.61667 -0.05115
   0.66781 -0.04624
   0.71704 -0.04120
   0.76375 -0.03605
   0.80734 -0.03083
   0.84723 -0.02542
   0.88326 -0.01958
   0.91560 -0.01369
   0.94380 -0.00854
   0.96708 -0.00447
   0.98478 -0.00168
   0.99608 -0.00033
   1.00000  0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

Joukovsky f=0% t=15%PreviewDetails
BOEING 737 ROOT AIRFOILPreviewDetails
E474 (14.09%)PreviewDetails
E169 (14.4%)PreviewDetails
NACA 0015PreviewDetails
EPPLER 473 AIRFOILPreviewDetails
S1048 14% (Danny Howell)PreviewDetails
OAF139 AIRFOILPreviewDetails
S8035 for RC aerobatic 14% thickPreviewDetails
FX LIII-142 K 25 AIRFOILPreviewDetails

Polars for E475 (15.01%) (e475-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   e475-il50,000920.2 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e475-il50,000524.1 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   e475-il100,000930.5 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e475-il100,000536.3 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   e475-il200,000946.2 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   e475-il200,000551.3 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
   e475-il500,000972.8 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e475-il500,000571 at α=10.5°Mach=0 Ncrit=5Xfoil predictionDetails
   e475-il1,000,000990 at α=11°Mach=0 Ncrit=9Xfoil predictionDetails
   e475-il1,000,000583.6 at α=10.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit