ADVANCED X-15A-2 ABLATION SYSTEM DESIGN, TESTS, AND ANALYSIS

Abstract

An investigation of ablation materials was conducted for application to an advanced, Mach 8 modification of the X-15 Research Airplane. Performance of the selected material, thermo-lag T-500, was evaluated in plasma tunnel tests and in flight tests. Estimates were made of required ablator weight and thicknesses at stagnation and non-stagnation areas of the Advanced X-15A-2. Performance data, resulting from actual flight tests, plasma tunnel tests and analytical predictions, were compared.

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Document Details

Document Type
Technical Report
Publication Date
Feb 16, 1965
Accession Number
AD0460484

Entities

People

  • H. Shatzkin
  • J. B. Bodne
  • P. O. Paxson
  • Robert H. Johnson

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Ablation
  • Ablative Materials
  • Aircrafts
  • Airplanes
  • Boundary Layer
  • Bow Shock
  • Fuselages
  • Heat Energy
  • Heat Shields
  • Heat Transfer
  • Leading Edges
  • Materials Laboratories
  • Measurement
  • Photographs
  • Research Aircraft
  • Shear Stresses
  • Test Facilities

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Engineering
  • Pulsed Power and Plasma Physics.