Accession Number:

ADA200516

Title:

Design of a New Contraction for the ARL (Aeronautical Research Laboratories) Low Speed Wind Tunnel

Descriptive Note:

Aerodynamics rept.

Corporate Author:

AERONAUTICAL RESEARCH LABS MELBOURNE (AUSTRALIA)

Personal Author(s):

Report Date:

1986-11-01

Pagination or Media Count:

43.0

Abstract:

A numerical method is developed for the solution of Stokes Streamfunction. The method is applied to the exisiting Low Speed Wind Tunnel LSWT contraction shape. The calculated wall pressure coefficient distribution is compared to experimental measurements to test the approximation of axial symmetry made for the octagonal sections and for the effects of neglecting viscous forces. Reasonable agreement is obtained. The existing contraction is known to suffer from intermittent boundary layer separation near the entry caused by adverse pressure gradients. A new contraction shape is suggested that uses the contraction ratio of the existing LSWT so that the new design can be installed within the existing LSWT in the form of an inner skin. The new design, which is about 10 longer than the existing contraction, has an adverse pressure gradient near the inlet which is about 15 of that of the existing contraction while the adverse pressure gradient near the exit is around the same value. Keywords Wind tunnel nozzles, Subsonic wind tunnels, Flow distribution, Australia.

Subject Categories:

  • Aerodynamics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE