Accession Number:

AD0423310

Title:

INVESTIGATION OF AIR INJECTION AS A MEANS OF PRODUCING SHOCK-COMPRESSION SYSTEMS IN SUPERSONIC INLETS,

Descriptive Note:

Corporate Author:

UNIVERSITY OF SOUTHERN CALIFORNIA LOS ANGELES ENGINEERING CENTER

Personal Author(s):

• Wallace,D. A.

Report Date:

1963-09-20

Pagination or Media Count:

12.0

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

Descriptors:

• *DUCT INLETS
• SUPERSONIC FLOW
• SUPERSONIC AIRCRAFT
• AIR BREATHING ENGINES(UNCONVENTIONAL)
• GUIDED MISSILES
• SHOCK WAVES
• CASCADE STRUCTURES
• AIR
• INJECTION
• JET MIXING FLOW

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE