FORCE TESTS ON A SEPARABLE-NOSE CREW ESCAPE CAPSULE IN PROXIMITY TO THE PARENT FUSELAGE AT MACH NUMBERS 1.5 THROUGH 4.5.

Abstract

Static forces tests were conducted in the 40-in. supersonic tunnel on a separable-nose crew escape capsule in the presence of the forward section of the airplane fuselage. The separation rocket jet plume was simulated with cold air. Data were obtained at Mach numbers from 1.5 through 4.5 at capsule angles of attack from -14 to 20 deg. The fuselage section, relative to the capsule, was positioned at several locations aft of the capsule at zero angle of attack. Reynold number, based on a model length of 18.1 in., ranged from 1,810,000 to 9, 410,000. Selected results are presented showing the effects of the fuselage section on the static longitudinal stability and drag characteristics of the capsule.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1966
Accession Number
AD0487406

Entities

People

  • Jerry H. Jones

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms
  • Autonomy
  • Weapons Technologies

DTIC Thesaurus Topics

  • Abstracts
  • Air Force
  • Aircrafts
  • Airframes
  • Classification
  • Commerce
  • Escape Capsules
  • Fuselages
  • Gas Dynamics
  • Government (Foreign)
  • Government Procurement
  • Governments
  • Instrumentation
  • Mach Number
  • Test Facilities
  • Trim Tabs
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Explosive Engineering.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow