Transition Measurements via Heat-Transfer Instrumentation on a 0.5 Bluntness 9.75-deg Cone at Mach 7 with and without Mass Addition

Abstract

A test was conducted at Mach number 7.2 on a blunt cone featuring porous skins for mass addition to the boundary layer. Transition location was determined in relation to variations of Reynolds number, mass flow, and angle of attack. As expected, transition locations were dependent upon angle of attack for the range of angles tested (0 to 5 deg). However, only the highest mass flow rate of 0.042 lbm/sec injected through the nose section produced significant effects on the location of transition.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1977
Accession Number
ADB021861

Entities

People

  • A. H. Boudreau

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Advanced Electronics

DTIC Thesaurus Topics

  • Acquisition
  • Air Force
  • Boundary Layer
  • Boundary Layer Transition
  • Data Acquisition
  • Dynamics
  • Electric Arcs
  • Engineering
  • Flow Fields
  • Flow Rate
  • Free Stream
  • Gas Dynamics
  • Heat Transfer
  • Instrumentation
  • Mach Number
  • Static Pressure
  • Test And Evaluation

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Mechanics and Fluid Dynamics.