Calculation and Measurement of Transonic Flows over Aerofoils with Novel Rear Sections
Abstract
A combined theoretical and experimental investigation in to transonic flows over aerofoils of advanced design is described. The experiments were performed at high subsonic speeds and over a wide range of Reynolds number up to 20 million on a number of aerofoils with rear pressure distributions of differing form and severity. Three families of aerofoils were studied, all of which are of 14% thickness and have a high degree of rear camber. Data for aerofoil pressure distributions and overall forces are compared with predictions by a calculation method based on the viscous-inviscid interaction concept and including allowance in the modelling of the turbulent shear layers for effects which become important as separation is approached. Predictions of pressure distributions by this method are shown to be in generally good agreement with experiment for the various sections tested, and it is concluded that the method provides a reliable basis for designing aerofoil sections with advanced features. Keywords: Wind tunnel test data; Mathematical prediction. Great Britain.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1988
- Accession Number
- ADA208859
Entities
People
- P. R. Ashill
Organizations
- Royal Aircraft Establishment