Accession Number:

ADA023353

Title:

Schlieren Diagnostics for the AFIT Hypersonic Shock Tunnel.

Descriptive Note:

Master's thesis,

Corporate Author:

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

Personal Author(s):

Report Date:

1974-09-01

Pagination or Media Count:

85.0

Abstract:

Visualization of Mach 10 and Mach 15 flow phenomena was accomplished using a Toepler schlieren system. The systems range and sensitivity were determined and related to the free-stream properties of the hypersonic flow over a wedge model. Schlieren photographs were taken using both a Polaroid camera and a high speed 16mm Fastax movie camera. An attempt was made using enlarged schlieren photographs to determine the test section Mach number from measured shock wave angles and measured flow deflection angles inclusive of the boundary layer displacement effect.

Subject Categories:

  • Test Facilities, Equipment and Methods
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE