Analysis of Wind Tunnel Test Results of Fluidic Generator for High-Altitude Rocket

Abstract

A ram-air-driven power supply for a proposed high-altitude rocket was tested in the Naval Surface Weapons Center supersonic wind tunnel facility. The wind tunnel data that corresponded to points on the trajectory providing the least ram-air energy showed that the generator operated throughout the test and produced a minimum of 26.4 Vrms into a simulated fuze load near the apex where pneumatic power input is minimal. A method of predicting generator voltage in flight from laboratory calibration data and expected flight conditions was verified for Mach numbers from 1.5 to 2.02 and free-stream total pressures of up to 20 lb/in sq in. abs (137 kPa).

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1979
Accession Number
ADA069172

Entities

People

  • Jonathan E. Fine

Organizations

  • Harry Diamond Laboratories

Tags

Communities of Interest

  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Altitude
  • Elevation
  • Energy
  • Flow
  • Flow Rate
  • Fluid Flow
  • Fluidic Generators
  • Free Stream
  • Generators
  • High Altitude
  • Mach Number
  • Power Supplies
  • Specific Heat
  • Supersonic Flow
  • Trajectories
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Electrical Engineering
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow