Transonic Conical Flow,

Abstract

The problem of inviscid, steady transonic conical flow formulated in terms of the small disturbance theory is studied. The small disturbance equation and similarity rules are presented, and a boundary value problem is formulated for the case of a supersonic freestream Mach number. The equation for the perturbation potential is solved numerically using an elliptic finite difference system. The difference equations are solved with a point relaxation algorithm that is also capable of capturing the shock wave during the iteration procedure by using the boundary conditions at the shock. Numerical calculations, for shock location, pressure distribution and drag coefficient, are presented for a family of nonlifting conical wings. The theory of slender wings is also presented and analytical results for pressure and drag coefficients are obtained. (Author)

Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1974
Accession Number
AD0784985

Entities

People

  • Kaloust Gregory Agopian

Organizations

  • University of California, Los Angeles

Tags

DTIC Thesaurus Topics

  • Algorithms
  • Boundaries
  • Boundary Value Problems
  • Coefficients
  • Conical Wings
  • Difference Equations
  • Differential Equations
  • Equations
  • Iterations
  • Mach Number
  • Mathematical Analysis
  • Mathematics
  • Pressure Distribution
  • Shock
  • Shock Waves

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow