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

S4110 (s4110-il)

S4110 - Selig S4110 low Reynolds number airfoil


Airfoil s4110-il
Details Dat file Parser  
(s4110-il) S4110
Selig S4110 low Reynolds number airfoil
Max thickness 8.4% at 26.6% chord.
Max camber 3.1% at 45.4% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
S4110
1.00000  0.00000
0.99677  0.00055
0.98738  0.00228
0.97242  0.00521
0.95237  0.00908
0.92746  0.01359
0.89794  0.01868
0.86424  0.02430
0.82685  0.03033
0.78630  0.03657
0.74310  0.04282
0.69771  0.04883
0.65062  0.05439
0.60225  0.05934
0.55306  0.06352
0.50349  0.06683
0.45401  0.06922
0.40507  0.07062
0.35714  0.07102
0.31066  0.07042
0.26612  0.06885
0.22394  0.06631
0.18453  0.06285
0.14830  0.05849
0.11555  0.05328
0.08659  0.04729
0.06167  0.04060
0.04093  0.03323
0.02437  0.02536
0.01204  0.01730
0.00400  0.00935
0.00021  0.00191
0.00000  0.00000
0.00119 -0.00408
0.00755 -0.00892
0.01905 -0.01317
0.03554 -0.01630
0.05723 -0.01820
0.08413 -0.01911
0.11599 -0.01920
0.15247 -0.01865
0.19313 -0.01757
0.23751 -0.01605
0.28509 -0.01417
0.33537 -0.01202
0.38774 -0.00970
0.44162 -0.00728
0.49640 -0.00487
0.55145 -0.00258
0.60606 -0.00053
0.65957  0.00121
0.71127  0.00260
0.76051  0.00360
0.80665  0.00418
0.84906  0.00436
0.88717  0.00416
0.92046  0.00363
0.94843  0.00285
0.97068  0.00193
0.98686  0.00102
0.99670  0.00029
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
GOE 565 AIRFOILPreviewDetails
S9037 (9%)PreviewDetails
Fage & Collins 1PreviewDetails
HOBIESMO1.DATPreviewDetails
S7075 (9%)PreviewDetails
SA7025PreviewDetails
GOE 515 AIRFOILPreviewDetails
S4053PreviewDetails
GOE 507 AIRFOILPreviewDetails

Polars for S4110 (s4110-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s4110-il50,000939.2 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   s4110-il50,000540.8 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s4110-il100,000960.1 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s4110-il100,000557.9 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s4110-il200,000981.4 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s4110-il200,000573.5 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s4110-il500,0009107.2 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   s4110-il500,000589.9 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s4110-il1,000,0009122.7 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s4110-il1,000,000599.9 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit