Transonic Kernel Function Method for Unsteady Flow Calculations Using a Unified Linear Pressure Panel Procedure.

Abstract

A transonic kernel function method for unsteady flow calculations has been developed. A unified linear presssure panel procedure is established to solve for two-dimensional problems in the subsonic, transonic, and supersonic flow regimes; consequently, a TLP2D computer code is developed. Numerical results are presented for pitching or flapping airfoils in these linear and nonlinear flow regimes. The mixed kernel function procedure is applied to a pitching Guderley airfoil in sonic flow. Comparisons with other results and discussions are given. Additional analytical studies include Landahl's general formulation of the phase correction method and the kernel function formulation of the Eckhaus-Landahl shock-jump model. Finally, assessments of and recommendations for the present work are given. (Author)

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1979
Accession Number
ADA080227

Entities

People

  • D. D. Liu
  • M. T. Landahl
  • W. S. Pi

Tags

Communities of Interest

  • Air Platforms
  • Counter IED
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Acoustic Waves
  • Air Force
  • Aircrafts
  • Bessel Functions
  • Computational Fluid Dynamics
  • Computational Science
  • Equations
  • Fluid Dynamics
  • Frequency
  • Integral Equations
  • Kernel Functions
  • Mach Number
  • Pressure Distribution
  • Shock Waves
  • Steady Flow
  • Three Dimensional
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Calculus or Mathematical Analysis
  • Fluid Dynamics.

Technology Areas

  • Hypersonics