Heat-Transfer, Surface-Pressure, and Boundary-Layer Surveys on Conic and Biconic Bodies with Boundary-Layer Trips at Mach Number 6. Phase 1

Abstract

Heat-transfer data were obtained on a 7-deg cone and a 14/7-deg biconic model to determine the minimum size distributed roughness required to bring boundary-layer transition near the model nose. Surface pressure and boundary-layer surveys were also obtained on a few configurations in an attempt to identify the difference in the characteristics of naturally turbulent boundary layers and those tripped with distributed roughness. Data were obtained at a nominal Mach number of 6 at Reynolds numbers ranging from 1,000,000 to 4, 700,000 per foot. Most of the data were obtained at zero angle of attack although some data were obtained at angle of attack for a few selected bluntness/trip combinations.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1978
Accession Number
ADA067908

Entities

People

  • Frederick K. Hube

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Data Acquisition
  • Data Reduction
  • Dynamic Pressure
  • Flow
  • Flow Fields
  • Geometry
  • Heat Transfer
  • Heat Transfer Coefficients
  • Instrumentation
  • Layers
  • Mach Number
  • Measurement
  • Pressure Measurement
  • Reynolds Number
  • Static Pressure
  • Test Facilities

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.