An Exploratory Investigation on Reducing Supersonic Missile Drag by Fluid Injection into a Turbulent Boundary Layer

Abstract

To determine general effects of fluid injection into a turbulent boundary layer on missile drag and stabilizing forces at angle of attack, an exploratory investigation was made at Mach 1.63 and 2.2. The test model was a body of revolution 10-cal long with a 3-cal tangent ogive nose and stabilizing fins. The mass injection was simulated by nitrogen and injected into the boundary layer from a porous section just aft of the nose body junction. The porous section was varied in length from 0.5 to 1.5 cal. Angle of attack range varied from -3.5 deg to +19 deg.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1976
Accession Number
ADA034522

Entities

People

  • Donald Rubin

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Acquisition
  • Aeronautical Engineering
  • Air Force
  • Base Pressure
  • Bodies
  • Boundary Layer
  • Corporations
  • Engineering
  • Fluid Dynamics
  • Jet Propulsion
  • Mach Number
  • Mechanical Engineering
  • New Jersey
  • Physics Laboratories
  • Pressure Measurement
  • Security
  • Turbulent Boundary Layer

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Internal Combustion Engine (ICE) Technology.
  • Ocean-Atmosphere Mesoscale Modeling, Data Assimilation, and Flux Boundary Layers

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers