The Development of a Small Mach 10 Hypersonic Wind Tunnel

Abstract

A hypersonic wind tunnel was constructed at the Gas Dynamics Laboratory using air as the working fluid. This tunnel, capable of operating from Mach 5 to 10 at Reynolds numbers per inch of 0.03 to 0.40 million, has a test section diameter of 3 1/4 inches. The key part of the installation is a storage heater which consists of a coil of heavy-walled inconel pipe which is preheated electrically to the desired stagnation temperature. A maximum temperature of 2000 R at a pressure of 1500 psia is generated for running times of 6 to 12 minutes. Preliminary calibration tests using conical nozzles at M = 7 and 10 have verified the basic design and operating range.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1963
Accession Number
AD0424293

Entities

People

  • I. E. Vas
  • N. A. Zarin

Organizations

  • Princeton University

Tags

Communities of Interest

  • Advanced Electronics
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Conical Nozzles
  • Flow
  • Gas Dynamics
  • Heat Energy
  • Heat Transfer
  • Heat Transfer Coefficients
  • High Pressure
  • Hypersonic Wind Tunnels
  • Mach Number
  • Mass Flow
  • Measurement
  • Pressure Measurement
  • Reynolds Number
  • Stagnation Pressure
  • Stagnation Temperature
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Rocket Propulsion.
  • Thermal Physics or Thermal Science.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow