Accession Number:

AD0716026

Title:

Supersonic Nozzle Design

Descriptive Note:

Corporate Author:

NAVAL ORDNANCE LAB WHITE OAK MD

Personal Author(s):

Report Date:

1970-09-22

Pagination or Media Count:

25.0

Abstract:

The paper is concerned with a method of finite differences for determining two-dimensional and axisymmetric supersonic nozzle contours. The approach taken is to specify a Mach number or velocity array along the entire centerline of the nozzle and then to integrate the equations numerically to obtain the desired nozzle shape. The original problem was tested in the subsonic region, and reasonable results were found provided the Mach number gradient was not too steep in a neighborhood of the sonic line.

Subject Categories:

  • Aerodynamics
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE