Roll-Damping Derivative Calculations for Spinning Sharp and Blunt Cones in Supersonic and Hypersonic Flow

Abstract

The boundary-layer equations in a Crocco variables form have been numerically solved for flow over spinning sharp and blunt cones at zero incidence to supersonic and hypersonic streams. Both laminar and turbulent flows have been treated, and for the blunt cases swallowing of the inviscid entropy layer by the boundary layer has been considered. The item of primary interest is roll damping, and results of a parametric study involving Mach number, Reynolds number, cone angle, and bluntness ratio are presented. Limited comparisons with experimental data and another method of computation are also presented.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1979
Accession Number
ADA065594

Entities

People

  • Arloe W. Mayne Jr.

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Bodies
  • Boundary Layer
  • Boundary Layer Flow
  • Computational Fluid Dynamics
  • Differential Equations
  • Equations
  • Experimental Data
  • Fluid Dynamics
  • Fluid Flow
  • Free Stream
  • Laminar Flow
  • Mach Number
  • Reynolds Number
  • Turbulent Flow
  • Viscous Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers