Unsteady compressible boundary layer flow over a circular cone near a plane of symmetry

A. J. Chamkha

2005

An analysis has been performed to study the unsteady laminar compressible boundary layer governing the hypersonic flow over a circular cone at an angle of attack near a plane of symmetry with either inflow or outflow in the presence of suction

Highlights

Powered by

Need more features? Check out our Chrome Extension and save interactive summary cards to your Scholarcy Library.