FORCE TESTS ON A SEPARABLE-NOSE CREW ESCAPE CAPSULE WITH COLD FLOW ROCKET JET SIMULATION AT MACH NUMBERS 1.5 THROUGH 6

Abstract

Static force tests were conducted in the 40-in. supersonic tunnel of the von Karman Gas Dynamics Facility on a separable-nose crew escape capsule having cold flow simulation of the separation rocket jet plume. Data were obtained at Mach numbers from 1.5 to 6 at angles of attack from -30 to 30 deg and angles of sideslip from -15 to 15 deg. Reynolds number, based on a model length of 18.1 in., ranged from 1,360,000 to 12,300,000. Selected results are presented showing the effects of the rocket exhaust jet on the static stability and drag characteristics of the vehicle.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1966
Accession Number
AD0481301

Entities

People

  • A. W. Myers
  • Jerry H. Jones
  • Leroy M. Jenke

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Air Force
  • Altitude
  • Contracts
  • Creep
  • Dynamics
  • Escape Capsules
  • Escape Systems
  • Flight
  • Gas Dynamics
  • Gases
  • Mach Number
  • Pressure Measurement
  • Reynolds Number
  • Rocket Exhaust
  • Simulations
  • Wind Tunnels

Fields of Study

  • Physics

Readers

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

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow