# 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