Aerodynamic and Thermal Performance Characteristics of Supersonic-X Type Decelerators at Mach Number 8

Abstract

Wind tunnel test results of the aerodynamic and thermal performance characteristics of model nylon, Kevlar 29, and Bisbenzimidaz0- benzophenanthroline Supersonic-X type parachutes behind a cone forebody at Mach = 8.0 are presented. The test was conducted at free-stream unit Reynolds numbers from 1.1 to 3.6 million per foot, simulating pressure altituded ranging from 145,000 to 130,000 ft, respectively. Drag data are presented which show increased axial force with increasing trailing distance and/or increasing dynamic pressure. Wake survey pressure and total temperature profiles are presented which show the symmetrical nature of the wake and the effects of the forebody mounting struts.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1977
Accession Number
ADB016529

Entities

People

  • J. D. Corce

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Air Force
  • Air Force Facilities
  • Data Reduction
  • Dynamic Pressure
  • Flow
  • Free Stream
  • Government Procurement
  • Governments
  • Mach Number
  • Materials
  • Measurement
  • Stagnation Temperature
  • Static Pressure
  • Test And Evaluation
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow