The Effect of Multi-mode Induced Transition in a Hypersonic Boundary Layers

Abstract

This study extends the work of Smith to Mach numbers indicative of the hypersonic flight regime and correlate the results to the occurrence of transition. The existing model uses PSE to capture the fully nonlinear interaction of modes in a low-speed, non-reacting, compressible boundary layer. It has the capability to calculate the contributions to surface heating and skin friction from the interaction of homogeneous (e.g. first-mode/second-mode) and inhomogeneous mode interaction (e.g. second-mode/crossflow). This approach captures the more realistic conditions that occur in-flight.

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Document Details

Document Type
Technical Report
Publication Date
Apr 02, 2019
Accession Number
AD1085761

Entities

People

  • Sonya T. Smith

Organizations

  • Howard University

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force Research Laboratories
  • Boundary Layer
  • Boundary Layer Flow
  • Boundary Layer Transition
  • Curvature
  • Flow Fields
  • Fluid Dynamics
  • Fluid Mechanics
  • Geometry
  • Heat Transfer
  • Hypersonic Flight
  • Hypersonic Missiles
  • Hypersonic Vehicles
  • Mechanics
  • Propulsion Systems
  • Reynolds Number
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Wave Propagation and Nonlinear Chaotic Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers