Effects of Cone Tip Changes on Wall-Cooled Hypersonic Boundary Layer Transition and Turbulence

Abstract

Boundary layer measurements took place at Air Force Research Labs (AFRL) Mach-6 Ludwieg tube hypersonic wind tunnel on a 7-degree half angle spherically blunted nose cone with a 1.5 mm radius to study the effects of a cooled surface on the transition process. Experiments compared uncooled and cooled flow conditions on the blunt-nosed model, and then compared to past data for a sharp-tipped cone of similar geometry. Cooling the surface delayed the onset of transition on the blunt nose model. Combining the effects of nose blunting and cooling further increased transition delay than each acting individually compared to the sharp-tipped case. This outcome provides much needed data in an area of study with inconclusive results.

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Document Details

Document Type
Technical Report
Publication Date
Mar 24, 2022
Accession Number
AD1175627

Entities

People

  • Mathew M. Major

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Energy and Power Technologies
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Research Laboratories
  • Boundary Layer
  • Boundary Layer Control
  • Boundary Layer Flow
  • Boundary Layer Transition
  • Change Detection
  • Computational Fluid Dynamics
  • Fluid Dynamics
  • Fluid Flow
  • Fluid Mechanics
  • Geometry
  • Hypersonic Wind Tunnels
  • Mechanics
  • Military Research
  • Physics Laboratories
  • Surface Properties
  • Test Facilities
  • Turbulent Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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