Accession Number:

AD0735066

Title:

Effect of Flow Discontinuities on Oscillatory Pressures Measured in Supersonic Wind Tunnels,

Descriptive Note:

Corporate Author:

NATIONAL AERONAUTICAL ESTABLISHMENT OTTAWA (ONTARIO)

Personal Author(s):

• Orlik-Rueckemann,K. J.
• LaBerge,J. G.

Report Date:

1969-10-13

Pagination or Media Count:

3.0

Abstract:

The effect of wind-tunnel flow discontinuities, which previously was considered to be a serious obstacle in measuring oscillatory surface pressures at supersonic speeds, was investigated. Results are reported for a particular nozzle in one tunnel.

Descriptors:

• (*SUPERSONIC WIND TUNNELS
• FLOW FIELDS)
• MODEL TESTS
• OSCILLATION
• PRESSURE
• AERODYNAMIC CONTROL SURFACES
• WIND TUNNEL NOZZLES
• TEST METHODS
• CANADA

Subject Categories:

• Test Facilities, Equipment and Methods

Distribution Statement:

APPROVED FOR PUBLIC RELEASE