Accession Number:

AD0254405

Title:

SHOCK-WAVE SYSTEMS

Descriptive Note:

Corporate Author:

LIBRARY OF CONGRESS WASHINGTON DC AEROSPACE TECHNOLOGY DIV

Personal Author(s):

Report Date:

1961-03-20

Pagination or Media Count:

1.0

Abstract:

The reduction of gas velocity in plane-parallel flow by means of a shock-wave system co turns the flow in the same direction. A calculation method makes possible the determination of the flow parameters behind the shock-wave system when the parameters in front of the systemARE GIVEN. The case is discussed in plane-parallel flow where the flow velocity M1 and the number of the shock waves m are given, and the sisting solely of a number of consecutive oblique shock waves is discussed. Intensity is equal for all shock waves of the system, and each oblique shock wave turns the flow in the same direction. A calculation method makes possible the determination of the flow parameters behind the shock-wave system when the parameters in front of the systemARE GIVEN. The case is discussed in plane-parallel flow where the flow velocity M1 and the number of the shock waves m are given, and the pressure, velocity, and the direction of the flow behind the shock-wave system are determined. The problem is solved by means of a general formula. Calculation results are presented in the form of six graphs depicting the characteristics of oblique shock waves for values of M1 from 3 to 5. The oblique shock-wave system discussed can be used advantageously in diffusers of aircraft engines to obtain optimum velocity-reducing systems with lower air temperatures in front of the compressor than those obtainable with a conventional normal shock-wave system. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE