The Effects of Viscosity on a Conically Derived Waverider

Abstract

This study investigated the effects of the interaction between the viscous boundary layer and the shock wave produced by a Mach 10 inviscid optimized waverider. An implicit, Roe flux-splitting algorithm, developed by WL/FIMM, was used to solve the flow field. A validation for the inviscid version of the CFD algorithm was accomplished by comparing the numerical -data produced by the CFD code to the analytic results derived by Rasmussen, and by comparison to results of the explicit version of the same Roe flux-splitting code. The computational results compared favorably. The inviscid case studied using the implicit code produced results identical, for all practical purposes, to those of the explicit code, though approximately twice as quickly. The results of the viscous flow case matched well with the results predicted by theory. The lift to drag ratio calculated, 5.74, is comparable to the results of other researchers.. .. Inviscid optimized waverider, Navier-stokes solution, Viscous flow, Hypersonic vehicle,

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1992
Accession Number
ADA259019

Entities

People

  • James A. Mundy

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Algorithms
  • Boundary Layer
  • Cartesian Coordinates
  • Computational Fluid Dynamics
  • Computational Science
  • Computers
  • Coordinate Systems
  • Flow Fields
  • Fluid Dynamics
  • Geometry
  • Heat Transfer
  • Layers
  • Shock Waves
  • Two Dimensional
  • Vehicles
  • Viscous Flow

Readers

  • Aerodynamics/Aeronautics.
  • Computational Fluid Dynamics (CFD)

Technology Areas

  • Hypersonics