INVESTIGATION OF AIR INJECTION AS A MEANS OF PRODUCING SHOCK-COMPRESSION SYSTEMS IN SUPERSONIC INLETS,
Abstract
From the investigation it was concluded that: (1) Air injected normal to a supersonic stream creates a two-shock supersonic, compression system similar to that created by a forward facing step in supersonic flow. (2) The degree of extension of the shock wave system into the primary flow is a function of the momentum of the injected air. (3) The stagnate air zone created downstream of the normal injector makes it difficult to position the transition normal shock waves in the region of maximum supersonic compression. (4) A cascade injector can be designed for efficient pressure recovery and avoids the stagnate region associated with the normal injector. This is accomplished however at the price of some degree of built-in contraction; and (5) The cascade injector is designed for high efficiency at one particular flow condition and may give poor performance if the inlet is intended for operation over a wide range of flight Mach numbers. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 20, 1963
- Accession Number
- AD0423310
Entities
People
- D. A. Wallace
Organizations
- University of Southern California