On the Design of Hypersonic Inward-Turning Inlets

Abstract

A family of dual-axis compression, high-contraction-ratio, inward-turning inlets has been designed to achieve a desired shock structure and aerodynamic performance at Mach 6. Computational simulations of the internal inlet flowfield were performed using the research code FDL3DI. These solutions are an integrated part of the inlet design methodology and offer insight into the fundamental fluid phenomenology. The effects of viscous/inviscid interactions, namely swept-shock/turbulent boundary layer interactions are discussed. Additionally, the importance of complementary computational fluid dynamics (CFD) to the experimental work as part of the integrated hypersonic inlet design process is also addressed.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 2007
Accession Number
ADA494010

Entities

People

  • Barry A. Croker

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Ground and Sea Platforms
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Air Force Research Laboratories
  • Aircrafts
  • Boundaries
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Layers
  • Mach Number
  • Physics Laboratories
  • Pressure Measurement
  • Simulations
  • Three Dimensional
  • Turbulent Boundary Layer

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Computational Fluid Dynamics (CFD)

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow