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

E201 (11.88%) (e201-il)

E201 (11.88%) - Eppler E201 low Reynolds number airfoil


Airfoil e201-il
Details Dat file Parser  
(e201-il) E201 (11.88%)
Eppler E201 low Reynolds number airfoil
Max thickness 11.9% at 30.8% chord.
Max camber 2.6% at 49.4% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
E201  (11.88%)               
   1.00000  0.00000
   0.99653  0.00058
   0.98650  0.00250
   0.97069  0.00589
   0.94977  0.01042
   0.92406  0.01565
   0.89369  0.02141
   0.85899  0.02771
   0.82048  0.03454
   0.77871  0.04176
   0.73427  0.04923
   0.68777  0.05677
   0.63984  0.06419
   0.59110  0.07122
   0.54222  0.07754
   0.49365  0.08271
   0.44572  0.08644
   0.39870  0.08855
   0.35285  0.08895
   0.30843  0.08764
   0.26565  0.08471
   0.22484  0.08042
   0.18642  0.07496
   0.15078  0.06847
   0.11828  0.06112
   0.08925  0.05305
   0.06396  0.04443
   0.04264  0.03545
   0.02547  0.02632
   0.01258  0.01731
   0.00407  0.00876
   0.00011  0.00128
   0.00187 -0.00488
   0.00964 -0.01046
   0.02258 -0.01574
   0.04055 -0.02041
   0.06341 -0.02437
   0.09097 -0.02756
   0.12298 -0.02993
   0.15916 -0.03149
   0.19915 -0.03227
   0.24253 -0.03228
   0.28883 -0.03157
   0.33753 -0.03010
   0.38823 -0.02776
   0.44069 -0.02471
   0.49439 -0.02131
   0.54864 -0.01783
   0.60272 -0.01444
   0.65591 -0.01125
   0.70749 -0.00839
   0.75676 -0.00591
   0.80305 -0.00386
   0.84572 -0.00225
   0.88416 -0.00107
   0.91782 -0.00027
   0.94625  0.00025
   0.96912  0.00051
   0.98602  0.00045
   0.99646  0.00017
   1.00000  0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

HQ 2.5/12 AIRFOILPreviewDetails
NACA 63-412 AIRFOILPreviewDetails
HQ 3.0/12 AIRFOILPreviewDetails
E195 (11.82%)PreviewDetails
LDS-2 AIRFOILPreviewDetails
HQ 2.0/12 AIRFOILPreviewDetails
SG6051PreviewDetails
CLARK V AIRFOILPreviewDetails
MH 120 11.57%PreviewDetails
RAF 31 AIRFOILPreviewDetails

Polars for E201 (11.88%) (e201-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   e201-il50,000934 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e201-il50,000533.9 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   e201-il100,000956.7 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e201-il100,000557 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   e201-il200,000980.4 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   e201-il200,000578.2 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   e201-il500,0009112 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   e201-il500,0005104.6 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   e201-il1,000,0009135.9 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   e201-il1,000,0005122.5 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit