AS5045 (15%)
New! Bulk download of polars in Excel format: as5045.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (1) | Similarly shaped airfoils
Plain Flapped Shapes: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Basic Data: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl | Curve fits | Lift curve slopes
Data source comparison (Codes, CFD, Wind tunnel)
Compressibility Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Roughness Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Plain Flap Effects: cl,max vs flap deflection: all flap chords | 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cl vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cm vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cd vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
DB Name: as5045
Family: Selig et. al.
Max thickness: 15.0% at x = 37.74% chord
Max camber: 1.0% at x = 24.74% chord
Available data sources:
JavaFoil+Calcfoil stall+Eppler ext transition
Wind Tunnel (Gopalarathnam and Selig, 1998)
AeroFoil
XFOIL ncrit=9
Notes:
Coordinates from UIUC Airfoil Coordinates Database https://m-selig.ae.illinois.edu/ads/coord_database.html
Wind tunnel data from Ashok Gopalarathnam and Michael Selig of the UIUC Applied Aerodynamics Department as documented here http://www.krnet.org/as504x/design.html. Airfoil model made by Steve Eberhart.