An Experimental Investigation at Supersonic Mach Numbers of Base Drag of Various Boattail Shapes with Simulated Base Rocket Exhaust.

Abstract

An experimental investigation was conducted to determine the effect of boattail geometry and simulated base rocket nozzle flow on overall base drag. All tests were performed at Mach numbers 2.50, 3.00 and 3.50. Reasonable prediction of base drag for the reported boattail shapes can be made by using approximate and empirical equations. A conical boattail produced less drag than the other boattail shapes investigated. The maximum nozzle stagnation to free- stream pressure ratio reported is 315. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1969
Accession Number
AD0855156

Entities

People

  • Joseph Huerta

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Base Pressure
  • Boundary Layer
  • Data Acquisition
  • Data Reduction
  • Equations
  • Flow
  • Flow Fields
  • Free Stream
  • Mach Number
  • Mass Flow
  • Method Of Characteristics
  • Pressure Distribution
  • Pressure Gradients
  • Rockets
  • Stagnation Pressure
  • Static Pressure
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Internal Combustion Engine (ICE) Technology.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow