F-15 Model Internozzle Dynamic Pressure Acquisition

Abstract

A dynamic pressure survey of a 4.7-percent model of the F-15 aircraft was conducted during buffeting of F-15 afterbody nozzle in the NASA LaRC's 16-foot tunnel to obtain insight into the internozzle dynamic pressure phenomena germane to closely spaced engine installations. This test consisted of varying the Mach number from 0.48 to 1.2, the nozzle pressure ratio from 1 to 5, and the angle of attack from 0 to 6 degrees. These conditions were measured at six locations on the afterbody using strain gauge pressure transducers. It was determined that the measured data were broadband random, strongly stationary, and correlated.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1984
Accession Number
ADA410139

Entities

People

  • David Banaszak
  • Leonard L. Shaw Jr
  • Phyllis Bolds

Organizations

  • Wright Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Acquisition
  • Air Force
  • Air Force Facilities
  • Air Force Research Laboratories
  • Aircrafts
  • Data Acquisition
  • Data Analysis
  • Dynamic Pressure
  • Frequency
  • Gages
  • Instrumentation
  • Measurement
  • Pressure Transducers
  • Probability Density Functions
  • Strain Gages
  • Transducers
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion and Flow Dynamics.
  • Fluid Dynamics.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster