Accession Number:

ADA243047

Title:

Surface Pressure Measurements on the Wing of a Wind Tunnel Model During Steady Rotation

Descriptive Note:

Technical memo.

Corporate Author:

AERONAUTICAL RESEARCH LABS MELBOURNE (AUSTRALIA)

Personal Author(s):

• Martin, C. A.
• Brian, G. J.

Report Date:

1991-07-01

Pagination or Media Count:

86.0

Abstract:

Wind tunnel measurements were conducted to determine the nature of the pressure distribution over the wing of a model of a basic training aircraft for a range of angles of attack and rotation rates representative of aircraft spinning conditions. The tests were carried out as part of a collaborative programme organised through The Technical Cooperation Programme and were conducted in the Spin Research Facility at the NASA Langley Research Center. Software for displaying the surface pressure distributions was developed at the Aeronautical Research Laboratory. This report presents pressure coefficient data obtained during the programme, in both numerical and graphical form.

Descriptors:

• *WINGS
• *AERODYNAMIC LOADING
• *SPINNING(MOTION)
• AIRCRAFT
• RATES
• RESEARCH FACILITIES
• ANGLE OF ATTACK
• PRESSURE MEASUREMENT
• SURFACE PROPERTIES
• COEFFICIENTS
• WIND TUNNEL TESTS
• MILITARY TRAINING
• AUSTRALIA
• FIXED WING AIRCRAFT
• ROTATION
• PRESSURE DISTRIBUTION
• WIND TUNNEL MODELS
• AERODYNAMIC CONTROL SURFACES
• MEASUREMENT
• TRAINING AIRCRAFT
• COMPUTER PROGRAMS
• STEADY STATE

Subject Categories:

• Aerodynamics
• Training Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE