Shock Management in Diverging Flow Passages by Blowing/Suction, Part 2: Applications

Abstract

A quasi-one-dimensional compressible-flow theory for controlling shock position in a diverging flow passage with supersonic inlet flow was reported in Part 1 (Sarimurat, M. N., and Dang, T. Q., “Shock Management in Diverging Flow Passages by Blowing/Suction, Part 1: Quasi-One-Dimensional Theory,” Journal of Propulsion and Power, Vol. 28, No. 6, 2012, pp. 1222–1229.). The theory can predict the amount offlowblowing/suction required to place the shock at a prescribed area ratio as the backpressure is varied. In Part 2, computational fluid dynamics is used to demonstrate the usefulness of this quasi-one-dimensional theory when applied to two-dimensional supersonic nozzles and supersonic cascades. The theory is first applied to inviscid flows inside a two-dimensional supersonic nozzle and a supersonic cascade, and very good agreement between the quasi-one-dimensional theory and twodimensional numerical solutions is obtained.Applications to viscous flows are also demonstrated, and it is shown that when the theory is applied using the effective flow area corrected for flow blockage due to boundary layers; the method can accurately predict the amount of blowing/suction required to control the shock location inside the flow passage.