Aerodynamic Characteristics of Several Flexible Decelerators at Mach Numbers from 1.8 to 2.5

Abstract

A test was conducted in a propulsion wind tunnel to determine the aerodynamic performance of four types of decelerators. Data were obtained at Mach numbers from 1.8 to 2.5 at free-stream dynamic pressures from 80 to 200 psf. Increasing the Mach number resulted in a decrease in the steady-state drag coefficient and an increase in the dynamics of the cross parachutes. At Mach number 2.5, increasing the free-stream dynamic pressure resulted in a decrease in the dynamics and an increase in the steady-state drag coefficient of the Supersonic X parachute.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1971
Accession Number
AD0879024

Entities

People

  • M. L. Homan

Organizations

  • Arnold Engineering Development Complex

Tags

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Air Force
  • Cameras
  • Coefficients
  • Data Reduction
  • Digital Data
  • Dynamic Pressure
  • Dynamics
  • Free Stream
  • Load Cells
  • Mach Number
  • Parachutes
  • Recording Systems
  • Statistical Analysis
  • Steady State
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow