Accession Number:

ADA023542

Title:

Hypersonic Shock Tunnel Performance Characteristics.

Descriptive Note:

Master's thesis,

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1974-11-01

Pagination or Media Count:

64.0

Abstract:

The desired goal was to state the initial conditions and throat diameters which are suitable for testing re-entry shape models or hypersonic glide shapes in the shock tunnel.

Subject Categories:

  • Test Facilities, Equipment and Methods

Distribution Statement:

APPROVED FOR PUBLIC RELEASE