A Comparative Study of Numerical Versus Analytical Waverider Solutions

Abstract

The WL/FIMM explicit, Roe flux-splitting Euler algorithm is applied to the inviscid hypersonic flow over a parabolic-top waverider configuration optimized for Mach 10 at zero degrees angle of attack. An on-design grid refinement study is conducted to determine the asymptotic nature of the optimized flight parameter L/D. A parametric study of off-design conditions is conducted to determine flow perturbation effects on HSDT waverider theory. A validation of the Euler code is conducted through a comparison of the numerical data to analytical results derived by Rasmussen. The grid refinement study shows little effect on the inviscid calculation of the optimized parameter L/D. Good agreement with HSDT waverider theory was attained for the on and off-design evaluations. Approximations involved in the numerical modeling of the waverider design produce large losses of lift as compared to the analytical results. Matching of the analytical results was possible only through a theoretical modeling process.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1991
Accession Number
ADA244183

Entities

People

  • Gregory O. Stecklein

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Base Pressure
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Computer Programs
  • Differential Equations
  • Euler Equations
  • Fluid Dynamics
  • Fluid Flow
  • Geometric Forms
  • Geometry
  • Hypersonic Aircraft
  • Numerical Analysis
  • Three Dimensional
  • Two Dimensional
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Computational Fluid Dynamics (CFD)

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow