INVESTIGATION OF F-111 CREW MODULE STABILIZATION PARACHUTE MODELS AT MACH NUMBERS OF 0.5, 2.0, 2.2, AND 2.5. PHASE I

Abstract

A test was conducted in the Propulsion Wind Tunnel, Supersonic (16S) to obtain drag, stability, and inflation characteristics of full-scale and quarter-scale models of proposed stabilization parachute configurations for the F-111 airplane crew module. The parachutes were fabric, ribbon-type models of the hemisflo family of parachutes with geometric porosities of the canopy of 15, 18, and 21%. The parachute characteristics were investigated at nominal Mach numbers of 0.5, 2.0, 2.2, and 2.5 at a nominal free-stream dynamic pressure of 120 psfa. Test results indicate that the drag coefficient of the full-scale and quarter-scale parachutes decreases as supersonic Mach number increases and that the stability of a quarter-scale parachute is better than the stability of a full-scale parachute for the same riser line length.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1965
Accession Number
AD0461730

Entities

People

  • Lawrence L. Galigher

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Aircrafts
  • Airplanes
  • Coefficients
  • Deployment
  • Dynamic Pressure
  • Free Stream
  • Government Procurement
  • Governments
  • Instrumentation
  • Mach Number
  • Models
  • Parachutes
  • Scale Models
  • Steady State
  • Test Facilities
  • Wind Tunnels

Readers

  • Aerial Delivery - Logistics and Supply Chain Management.
  • Aerospace Engineering
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow