Low Reynolds Number Hypersonic Testing in the NSWC Hypervelocity Wind Tunnel 9,

Abstract

The capabilities of the NSWC Hypervelocity Wind Tunnel 9 have been extended to simulate higher altitudes. A second ejector has been installed to allow operation at a supply pressure of 60 psia. Compression heating has been used to increase the supply temperature. High quality flow is obtained in a large core diameter. Static forces and moments on a subscale model have been successfully measured in a series of verification tests.

Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1984
Accession Number
ADP004796

Entities

People

  • E. R. Hedlund
  • R. L. P. Voisinet
  • W. C. Ragsdale

Organizations

  • Naval Ordnance Laboratory

Tags

DTIC Thesaurus Topics

  • Agreements
  • Air Force
  • Altitude
  • Compression
  • Diameters
  • Flow
  • Flow Fields
  • Maryland
  • Republic
  • Reynolds Number
  • Verification
  • Verification Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow