Accession Number:

ADA000415

Title:

A Study of the Nozzle Flow in a Large Arc-Heated Hypersonic Wind Tunnel.

Descriptive Note:

Technical rept. Jul 67-Dec 69,

Corporate Author:

AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OHIO

Personal Author(s):

• Van Kuren,James T.

Report Date:

1974-08-01

Pagination or Media Count:

139.0

Abstract:

The objective of the study was to obtain information about the flow of chemically reacting air that has been heated in a vortex stabilized, high voltage, direct current arc and expanded to hypersonic speeds in a conical nozzle. The inviscid core of the axisymmetric flow in the supersonic section of the nozzle was theoretically analyzed by the method of characteristics for air in chemical and thermal equilibrium. Impact pressure, mass flux, and heat transfer profiles and nozzle-wall static pressures were obtained. Light emissions from the reacting stream were recorded spectroscopically. Modified author abstract

Descriptors:

• *THERMAL PROPERTIES
• *HYPERSONIC WIND TUNNELS
• *NOZZLE GAS FLOW
• MATHEMATICAL MODELS
• PHOTOCHEMICAL REACTIONS
• PERFORMANCE(ENGINEERING)
• PRESSURE MEASUREMENT
• FLOW FIELDS
• LIGHT TRANSMISSION
• WIND TUNNEL TESTS
• HYPERSONIC CHARACTERISTICS
• INVISCID FLOW
• BOUNDARY LAYER FLOW
• ARC HEATERS
• WIND TUNNEL NOZZLES

Subject Categories:

• Test Facilities, Equipment and Methods
• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE