Accession Number:

AD0463276

Title:

THE AERODYNAMIC DESIGN OF AXISYMMETRIC NOZZLES FOR HIGH-TEMPERATURE AIR

Descriptive Note:

Technical Report

Corporate Author:

NAVAL ORDNANCE LAB WHITE OAK MD WHITE OAK

Personal Author(s):

Report Date:

1962-02-05

Pagination or Media Count:

96.0

Abstract:

A method is given for aerodynamic design of contoured axisymmetric nozzles by the method of characteristics, with a turbulent boundary layer correction, for high-temperature air in thermodynamic equilibrium. The method has been coded on an IBM 704 computer, and used to investigate boundary-layer growth and heat transfer in a family of hypervelocity nozzles having exit Mach numbers from 11 to 19, supply pressures from 50 to 500 atmospheres and supply temperatures up to 7500 K.

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE