Accession Number:

AD0750513

Title:

Controlling the Boundary Layer in Hypersonic Air Intakes

Descriptive Note:

Corporate Author:

FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH

Report Date:

1972-07-28

Pagination or Media Count:

14.0

Abstract:

An increase in the Mach number of airborne vehicles using airbreathing jet engines leads to a substantial decrease in the performance of the air intakes used in these engines. The main reason for the deterioration in performance is an increase in the influence of air viscosity. Despite the fact that the Mach number following compression in a hypersonic air intake intended for engines with supersonic combustion is greater than 1, the pressure ratio in it reaches p 100 and higher. In principle, such a pressure ratio can be obtained in a system of weak compression shocks with relatively low levels of total-pressure losses. However, the realization of such compression involves the occurrence of separation of the boundary layer. To prevent separation of the boundary layer a system for controlling the boundary layer must be devised.

Subject Categories:

  • Fluid Mechanics
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE