INVESTIGATION OF THE BOUNDARY CONDITION AT A WIND TUNNEL TEST SECTION WALL FOR A LIFTING WING BODY MODEL AT LOW SUPERSONIC SPEED. PHASE 1. TEST PREPARATIONS, REVISION OF COMPUTER PROGRAM AND EXPLORATORY COMPUTATIONS

The purpose of this investigation is to study experimentally and theoretically the flow field at locations around a lifting wing-body model, where wind-tunnel walls are normally situated. During Phase 1, which this report covers, the preparations for the experimental investigation have been carried out. The delta-wing-body model, the sting and support arrangement, a balance and a miniature flow inclination probe have been designed and manufactured. For the theoretical calculations a relaxation method based on the transonic small perturbation equation has been used. The computer program has been revised for supersonic free stream Mach numbers. The pressure and flow deflection angle have been calculated in the field near the wing-body configuration at Mach number 1.2 and at incidences of 0 deg and 5 deg. (Author)

• Corporate Authors:

  Aeronautical Research Institute of Sweden

  Stockholm,   Sweden 
• Authors:
  • Hedman, S G
  • Sorensen, H
  • Nyberg, S E
• Publication Date: 1978-2-24

Media Info

• Pagination: 34 p.

Subject/Index Terms

• TRT Terms: Aerodynamic lift; Boundary layer; Computer programs; Finite differences; Flow fields; Mechanical relaxation; Perturbations; Potential flow; Supersonic flow; Walls; Wind tunnels
• Geographic Terms: Sweden
• Old TRIS Terms: Delta wings; Transonic; Wing body configurations
• Subject Areas: Bridges and other structures; Materials;

Filing Info

• Accession Number: 00175957
• Record Type: Publication
• Source Agency: National Technical Information Service
• Report/Paper Numbers: FAA-AU-1432, AFOSR-TR-78-0605
• Contract Numbers: AFOSR-77-3282
• Files: NTIS
• Created Date: Jun 28 2002 12:00AM