Transition in Hypersonic Flows Including High-Temperature Gas Effects

Abstract

Hypersonic transition poses a special challenge for direct numerical simulations. Comparable data from Wind-tunnel tests or free-flight testing are not available or not accurate enough for comparison. The wind-tunnel testing does not allow for the exact match to the free-flight conditions at such high Mach-numbers. Flat-plate boundary-layer transition at high Mach-numbers is investigated in this work. A simulation case was chosen where chemical non-equilibrium plays an important role but ionization can be neglected. The chosen case at an altitude of H=50Km lies close to one point on the descent path of the Space Shuttle. The failure of the Space Shuttle has shown that an improved vehicle for space transportation is imperative in the close future. Transition research for an improved space-transportation vehicle is crucial in order to estimate the heat load during re-entry.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 2003
Accession Number
ADP014827

Entities

People

  • Christian Stemmer

Organizations

  • University of Technology

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Boundary Layer
  • Boundary Layer Flow
  • Boundary Layer Transition
  • Chemical Equilibrium
  • Computational Fluid Dynamics
  • Flow
  • Fluid Dynamics
  • Free Flight
  • High Temperature
  • Hypersonic Flow
  • Layers
  • Mach Number
  • Simulations
  • Space Shuttles
  • Space Transportation
  • Turbulence
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerospace Engineering.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flight
  • Hypersonics - Hypersonic Flow
  • Space
  • Space - Hall-Effect Thruster