Hostname: page-component-77c89778f8-sh8wx Total loading time: 0 Render date: 2024-07-17T04:03:04.984Z Has data issue: false hasContentIssue false
  • English
  • Français

A New Series of Aerofoil Sections Suitable for Aircraft Propellers

Published online by Cambridge University Press:  07 June 2016

A J Bocci
A J Bocci*
Affiliation:
Aircraft Research Association
Get access

Summary

A series of advanced aerofoil sections suitable for aircraft propellers has been developed. The sections combine advanced supercritical now characteristics with good low-speed performance and are also directly applicable to other rotating aerodynamic machinery, such as low-solidity ducted fans, windmills, etc. The work has focused initially on propeller sections of around 6 per cent thickness/chord ratio, typical of the fundamental blade station where peak loading is usually carried (0.7 × radius). The complete section family covers a wide range of thickness/chord ratios, from 3 per cent to over 20 per cent. The profiles are defined by mathematical formulae and distort with thickness to achieve a shape having optimum performance characteristics at the flow conditions expected for that thickness. A subset of the family is defined for higher Mach number penetration, up to near sonic values. Practical applications of the new sections have shown notable gains.

Type
Research Article
Information
Aeronautical Quarterly , Volume 28 , Issue 1 , February 1977 , pp. 59 - 73
Copyright
Copyright © Royal Aeronautical Society. 1977

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1 Glauert, H SBAC Standard Method of Propeller Performance Estimation.Google Scholar
2 Glauert, H The Elements of Aerofoil and Airscrew Theory. Cambridge University Press, 1947.Google Scholar
3 Bauer, F Garabedian, P Korn, D A theory of supercritical wing sections, with computer programs and examples. Lecture Notes in Economics and Mathematical Systems, No 66, Springer, 1972.CrossRefGoogle Scholar
4 Sells, C C L Plane subcriticai flow past a lifting aerofoil. RAE Technical Report 67146, 1967.Google Scholar
5 Powell, B J Calculation of the pressure distribution on a thick cambered aerofoil at subsonic speeds, including the effects of the boundary layer. NPL Aero Report 1238, 1967.Google Scholar
6 Horton, HP The calculation of the compressible turbulent boundary layer by the entrainment history method. Hawker Siddeley Aviation, HSA/Hatfield/Research/1048/HPH, 1969.Google Scholar