STABILITY DERIVATIVES OF 10 DEGREES PITCHING CONE IN HYPERSONIC VISCOUS FLOW.

Abstract

Using momentum integrals, an expression for the boundary layer displacement thickness is obtained from the unsteady equations of motion on a sharp, right, circular cone oscillating about a small mean angle of attack in hypersonic flow. The effects of the boundary layer displacement on the stability derivatives for small pitching oscillations were considered for an insulated cone with a Prandtl number of 1. Numerical results for a 10 degrees half-angle cone indicate that the viseous contributions to the stability derivatives may be considerable for low Reynolds numbers at high Mach numbers. (Author)

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1967
Accession Number
AD0833513

Entities

People

  • Grover D. Fulkerson

Organizations

  • Air Force Institute of Technology

Tags

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Displacement
  • Equations
  • Equations Of Motion
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Hypersonic Flow
  • Layers
  • Mach Number
  • Prandtl Number
  • Reynolds Number
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Microelectronics
  • Microelectronics - Graphene