Wind Tunnel Tests on Jindivik Air Intake Duct with and Without an Auxiliary Intake

Abstract

Results are presented for a wind tunnel program to investigate the effect of forward speed, incidence and yaw angle on the aerodynamic performance of an auxiliary air intake system fitted to the Jindivik target aircraft. Tests were carried out on a 1/4 scale model of an unmodified air intake duct, and one modified with several designs of auxiliary intake developed during static tests. The wind tunnel tests showed that worthwhile improvements in pressure recovery can be achieved at take-off speeds with simple intake modifications without excessive flow distortion at the engine face. In terms of pressure recovery at the engine face, performance improved with forward speed for all intake geometries tested. In the range of test parameters, the effects of both aircraft incidence and yaw were found to be negligible. Coefficients for distortion in total pressure distribution at the engine face were found to be within the acceptable range specified by the engine manufacturer.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1992
Accession Number
ADA251676

Entities

People

  • A. M. Abdel-fattah
  • Y. Y. Link

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Air Intakes
  • Air Masses
  • Aspect Ratio
  • Engineering
  • Flow
  • Free Stream
  • Geometry
  • Mass Flow
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Scale Models
  • Static Pressure
  • Static Tests
  • Steady State
  • Wind Tunnel Tests
  • Wind Tunnels

Readers

  • Aerodynamics/Aeronautics.