Pressure and Heat Transfer Measurements on Large Indented Nosetips.

Abstract

This report presents pressure and heat transfer data for 4 indented nosetip shapes. The tests were conducted in the NSWC Hypersonic Tunnel at Mach numbers 5 and 6. The report also presents an instrumentation technique developed as a result of a structural failure of one of the indented nosetip models. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1979
Accession Number
ADA088272

Entities

People

  • A. M. Morrison
  • Robert A. Kavetsky
  • W. C. Ragsdale

Organizations

  • Naval Ordnance Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Heating
  • Boundary Layer
  • Equations
  • Flow Fields
  • Fluid Dynamics
  • Fluid Flow
  • Free Stream
  • Heat Energy
  • Heat Transfer
  • Mechanics
  • Modulus Of Elasticity
  • Physics Laboratories
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Combustion and Flow Dynamics.
  • Technical Research and Report Writing.

Technology Areas

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