PRELIMINARY DESCRIPTION OF A HEATING SYSTEM FOR HYPERSONIC WIND TUNNELS FOR MACH NUMBERS BETWEEN 15 AND 30,

Abstract

From analysis it appears that a four stage supersonic compressor could be advantageously used for a hypersonic wind tunnel capable of achieving stagnation conditions of 100,000 to 150,000 psi and about 20,000 to 25,000R (ideal gas conditions) without the necessity of solving new technological problems. (Author)

Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1958
Accession Number
AD0685131

Entities

People

  • Antonio Ferri

Organizations

  • New York University Tandon School of Engineering

Tags

DTIC Thesaurus Topics

  • Buildings And Structures
  • Compressors
  • Hypersonic Wind Tunnels
  • Mach Number
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Systems Analysis and Design

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow