AERODYNAMIC PERFORMANCE OF VARIOUS HYPERFLO AND HEMISFLO PARACHUTES AT MACH NUMBERS FROM 1.8 TO 3.0

Abstract

As an extension of studies previously completed, a test was conducted in the Propulsion Wind Tunnel, Supersonic (16S), to determine the effect of Mach number on the drag, stability, and inflation characteristics of a number of parachutes. The parachute characteristics were investigated at Mach numbers from 1.8 to 3.0 at pressure altitudes from 82,000 to 104,000 ft. Two general types of parachutes were tested: the hyperflo-type parachute using three general design concepts with porosities from 7.0 to 10.9 percent and the hemisflo-type parachute with and without reefing. Data obtained indicated that the hyperflo parachutes had good inflation characteristics at Mach number 2.6 and the drag decreased with increasing Mach number. The hemisflo parachutes had good inflation characteristics in the 1.8 to 2.2 Mach number range. For any given configuration, the stability was found to be essentially constant with varying Mach number.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1965
Accession Number
AD0358325

Entities

People

  • David E. A. Reichenau

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Abstracts
  • Air Force
  • Contracts
  • Deployment
  • Governments
  • Load Cells
  • Mach Number
  • Materials
  • Motion Pictures
  • Parachutes
  • Photographs
  • Porosity
  • Research Facilities
  • Security
  • Steady State
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

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

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow