Simplified Solution of the Compressible Subsonic Lifting Surface Problem.

Abstract

A new technique for determining the spanwise and chordwise distribution of load, on thin finite wings in compressible subsonic flow, is presented. The method is based on the application of planar lifting surface theory. Classical theoretical results are used to define functions for the pressure coefficient distribution, and a new technique is presented for evaluating the kernel function integral. Analytical results are compared with experimental data and with solutions from a standard numerical integration method of applying lifting surface theory. Excellent correlation with experimental results is obtained for Mach numbers up to 0.80 to 0.85 for thin wings. Advantages of the new technique as opposed to other methods are also presented.

Document Details

Document Type
Technical Report
Publication Date
May 01, 1976
Accession Number
ADA027514

Entities

People

  • J. W. Purvis

Organizations

  • Naval Surface Warfare Center Dahlgren Division

Tags

DTIC Thesaurus Topics

  • Coefficients
  • Experimental Data
  • Flow
  • Integrals
  • Kernel Functions
  • Lifting Surfaces
  • Mach Number
  • Mathematics
  • Numerical Integration
  • Standards
  • Subsonic Flow
  • Surfaces
  • Thin Wings

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Approximation Theory.
  • Computational Fluid Dynamics (CFD)