INVESTIGATION OF AN INFLATABLE DECELERATOR ATTACHED TO A 120-DEG CONICAL ENTRY CAPSULE AT MACH NUMBERS FROM 2.55 TO 4.40

Abstract

A test was conducted in the 16-ft supersonic wind tunnel to obtain deployment, inflation, and steady-state characteristics of an inflatable decelerator attached to the base of an aeroshell entry capsule. Deployments were made at Mach numbers of 3.0 and 4.4 at free-stream dynamic pressures of 120 and 73 psfa, respectively. The preinflation method utilizing vaporization of sufficient liquid solution to completely inflate the decelerator volume resulted in successful deployments of the two decelerators. The decelerators remained fully inflated after each deployment and exhibited excellent stability.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1968
Accession Number
AD0841099

Entities

People

  • D. C. Baker

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Air Force
  • Cameras
  • Deployment
  • Dynamic Pressure
  • Fluids
  • Free Stream
  • Government Procurement
  • Governments
  • Instrumentation
  • Mach Number
  • Network Topology
  • Photographs
  • Static Pressure
  • Steady State
  • Supersonic Wind Tunnels
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerial Delivery - Logistics and Supply Chain Management.
  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow