Aeromechanical Properties of Ejection Seat Escape Systems

Abstract

Valid prediction of combat aircraft ejection seat performance has been impossible because of the lack of technical data on its basic physical properties and aerodynamic characteristics. Wind tunnel tests were conducted using a full scale F-101 ejection seat and a half scale F-106 ejection seat to determine the aerodynamic characteristics. Data were obtained at free stream Mach numbers of 0.2, 0.4, 0.6 and 0.8 for the full scale model and 0.6, 0.9, 1.2 and 1.5 for the half scale model. Angle of attack was varied from 0 to 360 degrees for the half scale model and -45 and +90 degrees for the full scale model. Yaw angles were varied from 0 to 45 degrees. The shape of the rocket catapult exhaust plume was simulated by using high pressure air.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1974
Accession Number
AD0787194

Entities

People

  • Bobby J. White

Organizations

  • Flight Dynamics Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Air Force
  • Aircrafts
  • Center Of Gravity
  • Dynamic Pressure
  • Ejection Seats
  • Escape Systems
  • Mach Number
  • Plastic Explosives
  • Rocket Exhaust
  • Sea Level
  • Test Facilities
  • Three Dimensional
  • Vehicle Equipment
  • Wind Tunnel Models
  • Wind Tunnel Tests
  • Wind Tunnels

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Engineering
  • Aviation Science / Aeronautics.