Passive Nosetip Technology (PANT) Program. Volume 14. An Experimental Study to Evaluate the Irregular Nosetip Shape Regime - Data Report

Abstract

Hypersonic wind tunnel tests conducted in the Naval Ordnance Laboratory Tunnel No. 8 are described. Thirty low temperature ablator (LTA) models were tested at Mach 5, with total temperatures between 493 deg F and 1013 deg F and free stream unit Reynolds numbers from 0.77 million to 15.70 million per ft. The Reynolds number regime for the formation of irregular shapes was found to be significantly influenced by nosetip size (nose radius) and wall temperature ratio (boundary layer edge to wall).

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1974
Accession Number
ADA020712

Entities

People

  • D. Chan
  • E. V. Nelson
  • T. C. Derbidge

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Boundary Layer
  • Bow Shock
  • Cameras
  • Computational Fluid Dynamics
  • Flow Fields
  • Geometry
  • Heat Transfer
  • Low Temperature
  • Motion Picture Photography
  • Photographs
  • Photography
  • Recording Systems
  • Surface Roughness
  • Test Facilities
  • Unsteady Flow
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Thermal Physics or Thermal Science.
  • Unmanned Aerial System (UAS) Autonomous Capabilities and Mission Reconnaissance.

Technology Areas

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