Second-Order Theory for a Thin Wing in Supersonic Flow with a Weak Spanwise Entropy Gradients,

Abstract

The three-dimensional perturbation velocities over an infinite thin wing with a sharp leading edge in non-uniform supersonic flow are derived and used to investigate the second-order contribution to the pressure coefficient on a wing surface, due to a spanwise entropy gradient. Pressure distributions are calculated for a wedge section wing at various Mach numbers for probable values of entropy gradient. Results show that entropy gradient effects can be important. Procedure for application of the theory is given for the case of a wing situated behind the curved shock generated by a blunt nosed body. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1961
Accession Number
AD0267914

Entities

People

  • Peter G. Wilby

Organizations

  • National Aeronautical Research Institute

Tags

DTIC Thesaurus Topics

  • Coefficients
  • Flow
  • Leading Edges
  • Mach Number
  • Motion
  • Perturbations
  • Physical Properties
  • Pressure Distribution
  • Supersonic Flow
  • Thin Wings
  • Three Dimensional

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Statistical inference.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow