Development of a Test to Evaluate Aerothermal Response of Materials to Hypersonic Flow Using a Scramjet Wind Tunnel (Postprint)

Abstract

A methodology to evaluate the aerothermal response of sharp leading edge materials by exposing them directly to hypersonic flow up to Mach 7 was developed and evaluated. The exposure was conducted using a prototype scramjet engine as a wind tunnel. A sample holder was designed using combustion fluid dynamics results as inputs into structural models. The rig conditions were evaluated and found to be close to those during free flight, with respect to aerothermal parameters of importance for material survivability. Samples of ultra high-temperature ceramics and SiC were found to withstand the short-term exposure that simulated Mach 6.5 at 25 km altitude.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 2010
Accession Number
ADA614592

Entities

People

  • George Jefferson
  • M. D. Petry
  • Mark R. Gruber
  • Michael K. Cinibulk
  • Tarun Mathur
  • Triplicane A. Parthasarathy

Organizations

  • Universal Energy Systems

Tags

Communities of Interest

  • Air Platforms
  • Ground and Sea Platforms

DTIC Thesaurus Topics

  • Air Force
  • Air Force Research Laboratories
  • Chemistry
  • Combustion
  • Composite Materials
  • Computational Fluid Dynamics
  • Fluid Dynamics
  • Fluid Flow
  • Free Flight
  • High Temperature
  • Hypersonic Flow
  • Leading Edges
  • Materials
  • Supersonic Combustion Ramjet Engines
  • Test Facilities
  • Test Methods
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Thin Film Deposition Science.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow