Design and Cold-Flow Evaluation of a Miniature Mach 4 Ramjet

Abstract

Methods used for designing the ramjet included conic shock tables; isentropic flow tables and the GASTURB code was used for aerothermodynamic performance prediction. The flow field through the proposed geometry was computed using the OVERFLOW code, and small modifications were made. Geometry and solid models were created and built using SolidWorks 3D solid modeling software. A prototype ramjet was manufactured with wind tunnel mounting struts capable of measuring axial force on the model. Shadowgraph photography was used in the Mach 4 supersonic wind tunnel at the Naval Postgraduate School's Turbopropulsion Laboratory to verify predicted shock placement, and surface flow visualization was obtained of the airflow from fuel injection ports on the inlet cone of the model. All indications are that the cold-flow tests were successful.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 2003
Accession Number
ADA417466

Entities

People

  • Kevin M. Ferguson

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms
  • Autonomy
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Combustion
  • Computational Fluid Dynamics
  • Creep
  • Flow Visualization
  • Fluid Dynamics
  • Fuel Injection
  • Fuel Systems
  • Geometry
  • Ramjet Engines
  • Spreadsheet Software
  • Three Dimensional
  • Turbines
  • Turbojet Engines
  • Viscous Flow
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Rocket Propulsion.
  • Software Engineering

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow