ESDU Transonic Aerodynamics Series

The information is concerned with the flow around aerofoils, wings, bodies and cowls at high subsonic, transonic and (in a few cases) low supersonic speeds. The transition from high subsonic to transonic flow is marked by the development of a local region of supersonic flow embedded in the otherwise wholly subsonic flow and the consequent development of shock waves and shock wave drag.

Methods in computational fluid dynamics (CFD) are important in the study of transonic aerodynamics, and information is provided concerning the use of such methods. Example results are given that demonstrate the accuracy that can be achieved for both inviscid and viscous flow. The Sections provide methods of calculating the pressure distribution and loading on aerofoils and wings in high subsonic flow, provide methods of calculating the drag-rise Mach number and/or the wave drag of aerofoils, wings and bodies, and provide exchange rates between pertinent aerofoil and wing design parameters at the drag-rise condition. For aerofoils and wings, particular attention is paid to the prediction of shock-induced separation and both direct (CFD) prediction and semi-empirical methods are given.

CFD has also been used to provide data for the wave drag coefficient for families of low fineness ratio forebodies and for an extensive family of axisymmetric forecowls. The data demonstrate how the pressure distribution and shock waves develop on the forebodies and forecowls considered as the Mach number is increased and as detailed changes in geometry are made.

A unique feature is the extensive treatment of the application of vortex generators to the control of shock-induced separation, particularly on wings, which includes consideration of the aerodynamic principles involved, a design guide and case studies of the use of vortex generators.