Linearized Compressible-Flow Theory for Sonic Flight Speeds

Abstract

The partial differential equation for the perturbation velocity potential is examined for free-stream Mach numbers close to ana equal to one. It is found that, under the assumptions of linearized theory, solutions can be found consistent with the theory for lifting-surface problems both in stationary three-dimensional flow and in unsteady two-dimensional flow. Several examples are solved including a three-dimensional swept-back wing and a two-dimensional harmonically oscillating wing, both for a free-stream Mach nuniber equal to one.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1949
Accession Number
ADA380626

Entities

People

  • Harvard Lomax
  • John R. Spreiter
  • Max A. Heaslet

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Aspect Ratio
  • Boundary Value Problems
  • Computational Science
  • Delta Wings
  • Differential Equations
  • Equations
  • Flight Speeds
  • Geometry
  • Load Distribution
  • Mach Number
  • Partial Differential Equations
  • Pressure Distribution
  • Steady State
  • Sweptback Wings
  • Three Dimensional
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Calculus or Mathematical Analysis
  • Fluid Mechanics and Fluid Dynamics.