DEVELOPMENT OF A HIGH SPEED INDUCTION TYPE WIND TUNNEL,

Abstract

The document describes the design, construction and operating performance of a high speed (0.8 Mach) open circuit induction type wind tunnel. The tunnel was developed primarily to test ram air submerged scoops used in heat exchange cooling systems. A tunnel wall simulates the airplane surface for this type of test. An instrumentation system was developed to record pressures for evaluating boundary layer parameters, ram air system wake drag and internal performance. (Author)

Document Details

Document Type
Technical Report
Publication Date
Sep 11, 1969
Accession Number
AD0693615

Entities

People

  • S. Strandbygaard

Organizations

  • Boeing Commercial Airplanes

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Airplanes
  • Boundaries
  • Boundary Layer
  • Construction
  • Fixed Wing Aircraft
  • Instrumentation
  • Layers
  • Wind Tunnels

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.
  • Software Engineering