An Empirical Equation for Prediction of Transition Location on Cones in Super-or Hypersonic Flight

Abstract

An empirical equation has been developed for the prediction of transition location on blunt and sharp cones. The equation predicts the transition location fairly well for 48 ballistics range tests for cones without ablation and for 40 flight tests for cones with ablation ranging from zero to large. The equation is applicable for cones in supersonic or hypersonic flight. The experimental data cover a range of local Mach numbers at transition from 2.8 to 14.7 and a range of the ratio of local wall to local stream temperature at transition from .074 to 1.43.

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Document Details

Document Type
Technical Report
Publication Date
Jun 14, 1973
Accession Number
AD0765692

Entities

People

  • Neal Tetervin

Organizations

  • Naval Ordnance Laboratory

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Boundary Layer
  • Boundary Layer Flow
  • Drag
  • Experimental Data
  • Flow
  • Free Stream
  • Geometry
  • Hypersonic Flight
  • Identification
  • Incompressible Flow
  • Kinetic Energy
  • Laminar Boundary Layer
  • Layers
  • Mach Number
  • Munitions
  • Ordnance Laboratories
  • Reynolds Number

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Control Systems Engineering.
  • Explosive Engineering.

Technology Areas

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