Investigation of an Attached Inflatable Decelerator with Mechanically Deployed Inlets at Mach Numbers from 2.25 to 4.75

Abstract

A test was conducted in the 16-ft supersonic wind tunnel to obtain deployment, inflation, and steady-state characteristics of an attached inflatable decelerator with mechanically deployed inlets. Deployments were made at Mach numbers 3.0 and 4.4 at free-stream dynamic pressures of 120 and 73 psf, respectively. The mechanically deployed inlet system resulted in successful deployments of the three test models with inflation times of from 0.4 to 0.7 sec.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1969
Accession Number
AD0854437

Entities

People

  • D. C. Baker

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Ground and Sea Platforms

DTIC Thesaurus Topics

  • Air Force
  • Cameras
  • Deployment
  • Dynamic Pressure
  • Export Controls
  • Free Stream
  • Government (Foreign)
  • Government Procurement
  • Governments
  • Instrumentation
  • Internal Pressure
  • Mach Number
  • Photographs
  • Steady State
  • Supersonic Wind Tunnels
  • Test Facilities
  • Wind Tunnels

Readers

  • Aerodynamics/Aeronautics.
  • Cardiovascular Physiology

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow