Advanced Ejection Seat for High Dynamic Pressure Escape. Wind Tunnel Test Report.

Abstract

Wind tunnel tests were conducted to evaluate new high dynamic pressure protective devices incorporated into a conventional ejection seat. These tests are part of a development program 'Advanced Ejection Seat for High Dynamic Pressure Escape'. The objectives of this program are to develop an ejection seat design which will provide safe escape during emergency conditions encountered throughout the performance envelope of an aircraft with speed capability to 687 KEAS. Preliminary phases of this program have resulted in selection and definition of a windblast-shield, an aft body drag reduction boom, a horizontal stabilizer and a flow diverter. These devices were incorporated into a one-half scale ejection seat/crewmember model and were tested in the AEDC PWT 16-T transonic tunnel. Aerodynamic data derived from these tests are being used in six-degree-of-freedom computer simulations for performance assessments of the ejection seat configurations. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1980
Accession Number
ADA091810

Entities

People

  • David T. Ther
  • John O. Bull
  • Roger F. Yurczyk

Organizations

  • Boeing Military Aircraft

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Air Force
  • Aircrafts
  • Center Of Gravity
  • Digital Information
  • Drag Reduction
  • Dynamic Pressure
  • Ejection Seats
  • Flow Visualization
  • Horizontal Stabilizers
  • Measurement
  • Sea Level
  • Test Facilities
  • Three Dimensional
  • Vehicle Equipment
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Engineering

Readers

  • Aerospace Engineering
  • Fluid Dynamics.
  • Materials Science