ANALYSIS OF TRANSONIC FLOW BY MEANS OF PARAMETRIC DIFFERENTIATION.

Abstract

A general method of solving nonlinear partial differential equations was developed and applied to the problem of inviscid transonic flow about airfoils. Soultions are given for nonlifting airfoils at all transonic Mach numbers, including those flows with detached shock waves, and extensions to include lifting and unsteady flows are discussed. Results are given for subsonic and supersonic flow, and for flows at Mach number unity which are in general agreement with other theoretical results and with experiment. Inadequacies in the numerical technique prevented the accurate computation of shock movements, but prelimiliminary results indicate a rearward movement of the shock impinging on the airfoil surface with increasing airfoil thickness, and exhibit the commonly observed rapid acceleration behind the shock. The well known local linearization result of Spreiter and Alksne is shown to be an approximation to the present theory for subsonic flow.

Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1965
Accession Number
AD0626058

Entities

People

  • Paul E. Rubbert

Tags

DTIC Thesaurus Topics

  • Differential Equations
  • Equations
  • Flow
  • Mach Number
  • Partial Differential Equations
  • Shock
  • Shock Waves
  • Subsonic Flow
  • Supersonic Flow
  • Transonic Flow
  • Unsteady Flow

Fields of Study

  • Physics

Readers

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

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow