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

S4053 (s4053-il)

S4053 - Selig S4053 low Reynolds number airfoil


Airfoil s4053-il
Details Dat file Parser  
(s4053-il) S4053
Selig S4053 low Reynolds number airfoil
Max thickness 8.9% at 30.9% chord.
Max camber 3% at 45% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
S4053
1.00000  0.00000
0.99662  0.00053
0.98686  0.00231
0.97153  0.00538
0.95119  0.00935
0.92601  0.01381
0.89611  0.01877
0.86192  0.02422
0.82393  0.03011
0.78266  0.03632
0.73869  0.04271
0.69260  0.04911
0.64500  0.05531
0.59647  0.06102
0.54753  0.06592
0.49853  0.06973
0.44977  0.07232
0.40160  0.07368
0.35444  0.07383
0.30868  0.07280
0.26476  0.07066
0.22310  0.06749
0.18409  0.06333
0.14813  0.05828
0.11551  0.05243
0.08655  0.04588
0.06147  0.03879
0.04053  0.03131
0.02388  0.02360
0.01163  0.01584
0.00377  0.00823
0.00013  0.00131
0.00000  0.00000
0.00152 -0.00393
0.00876 -0.00781
0.02265 -0.01116
0.03990 -0.01388
0.06334 -0.01592
0.09177 -0.01729
0.12494 -0.01808
0.16249 -0.01840
0.20391 -0.01829
0.24875 -0.01771
0.29661 -0.01671
0.34698 -0.01541
0.39927 -0.01392
0.45286 -0.01231
0.50711 -0.01064
0.56138 -0.00896
0.61507 -0.00731
0.66752 -0.00579
0.71809 -0.00443
0.76614 -0.00328
0.81105 -0.00236
0.85226 -0.00165
0.88923 -0.00113
0.92145 -0.00075
0.94854 -0.00041
0.97028 -0.00003
0.98646  0.00018
0.99655  0.00010
1.00000  0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

E176 (8.83%)PreviewDetails
E387PreviewDetails
E174 (Dicke 8.92%)PreviewDetails
SD6080 (9.2%)PreviewDetails
S7075 (9%)PreviewDetails
S3025 9.38%PreviewDetails
SA7038PreviewDetails
S9037 (9%)PreviewDetails
DormoyPreviewDetails
GOE 507 AIRFOILPreviewDetails

Polars for S4053 (s4053-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s4053-il50,000938.2 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   s4053-il50,000539.2 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s4053-il100,000958.9 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s4053-il100,000557.8 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s4053-il200,000980.6 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s4053-il200,000575.6 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s4053-il500,0009109.1 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s4053-il500,000596.5 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s4053-il1,000,0009129 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s4053-il1,000,0005109.6 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit