WIND TUNNEL INVESTIGATION OF FLEXIBLE AERODYNAMIC DECELERATOR CHARACTERISTICS AT MACH NUMBERS 1.5 TO 6

Abstract

Tests were conducted in the 40-in. supersonic Tunnel A of the von Karman Gas Dynamics Facility to investigate the drag and stability characteristics of a series of flexible decelerator models. The models were tested at Mach numbers from 1.5 to 6 at dynamic pressures corresponding to pressure altitudes of 75,000 to 135,000 ft, respectively. Four basic decelerator configurations were examined: hyperflo parachutes at variable locations aft of three fore body models, hemisflo parachutes with varied amounts of canopy inlet reefing, a tandem configuration composed of a hyperflo parachute inside the suspension lines of a hemisflo parachute, and a conical ballute decelerator.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1965
Accession Number
AD0464786

Entities

People

  • E. E. Hilliard
  • J. S. Deitering

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Altitude
  • Cameras
  • Dynamic Pressure
  • Dynamics
  • Gas Dynamics
  • Instrumentation
  • Internal Pressure
  • Mach Number
  • Motion Picture Cameras
  • Parachute Canopies
  • Parachutes
  • Photographs
  • Pressure Measurement
  • Static Pressure
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

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

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow