WEIGHT FLOW RATES THROUGH CIRCULAR HOLES IN A FLAT PLATE IMMERSED IN A SUBSONIC OR SUPERSONIC AIRSTREAM

Abstract

Results are presented of an investigation conducted in the Naval Ordnance Laboratory's Supersonic Tunnel No. 2 to measure the weight flow of air through various sized holes in a flat plate exposed to a flow parallel to the plane of the plate. These data were obtained at free-stream Mach numbers of 0.50 and 1.53 for various static pressure ratios across the flat plate. Results indicated that the measured weight flow rate decreases as the parallel flow Mach number increases. Increasing the parallel flow velocity from zero to supersonic may more than halve the flow discharge coefficient for a given pressure ratio across the hole. The effect of the parallel flow Mach number on the flow discharge coefficient is much greater than the effect of the hole thickness to diameter ratio for t/d <1.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Aug 08, 1963
Accession Number
AD0426097

Entities

People

  • A. P. Leonas
  • C. A. Kalivretenos
  • N. P. Frandsen

Organizations

  • Naval Ordnance Laboratory

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Facilities
  • California
  • Flow Rate
  • Free Stream
  • Instrumentation
  • Mach Number
  • Measurement
  • Naval Operations
  • Navy
  • New Jersey
  • Static Pressure
  • Steady State
  • United States
  • Weapons
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.

Technology Areas

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