Approximate Corrections for the Effects of Compressibility on the Subsonic Stability Derivatives of Swept Wings

Abstract

A method which has previously been presented for the estimation of the low-speed stability derivatives of swept wings is modified by means of the Prandtl-Glauert rule to yield approximate corrections for the first-order three-dimensional effects of compressible flow in the subsonic region. Corrections are presented in chart form for several aspect ratios and angles of sweep and may be computed rather simply for other aspect ratios and angles of sweep. Lift-curve slopes and values of damping in roll are compared with those obtained by use of a generally accepted method and are discussed in relation to unpublished data.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1949
Accession Number
ADA380763

Entities

People

  • Lewis R. Fisher

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Air Force
  • Air Force Facilities
  • Aircrafts
  • Aspect Ratio
  • Coefficients
  • Compressible Flow
  • Compressive Properties
  • Equations
  • Experimental Data
  • Flow
  • Free Stream
  • Incompressible Flow
  • Mach Number
  • Swept Wings
  • Three Dimensional
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.
  • Theoretical Analysis.