No CrossRef data available.
Article contents
Determination of Velocity and Pressure Distribution along the Surface of Annular Aerofoils with Thick Symmetrical Sections
Published online by Cambridge University Press: 28 July 2016
Extract
An approximate method is shown for the estimation of the velocity and pressure distribution over the surface of circular annular aerofoils with thick symmetrical sections, at zero incidence.
Figure 1 shows an annular aerofoil or profiled ring obtained when an aerofoil with symmetrical section rotates about an axis.
From the theory of wing sections it is known that the aerodynamic effect of a symmetrical aerofoil section, at zero angle of attack, may be approximately replaced by the effect of sources and sinks distributed along the chord of the section.
- Type
- Technical Notes
- Information
- Copyright
- Copyright © Royal Aeronautical Society 1956
References
1.
Allen, I. (1945). General Theory of Airfoil Sections having Arbitrary Shape or Pressure Distribution. N.A.C.A. Rep. 833, Washington, 1945.Google Scholar
2.
Küchemann, D. and Weber, J. (1953). Aerodynamics of Propulsion.
McGraw-Hill, New York, 1953.Google Scholar
3.
Pivko, S. (1955). Estimation of Velocity and Pressure Distribution over the Surface of Annular Airfoil with Thick Symmetrical Sections, at Zero Angle of Attack. Aerotechnical Institute, Tech. Note VS-086, Beograd, 1955.Google Scholar
4.
Abbott, I., Doenhoff, A. and Stivers, L. (1945). Summary of Airfoil Data. N.A.C.A. Rep. 824, Washington, 1945.Google Scholar