Test Results from the Pressure Phase of the Flow Diagnostics Applications Test Conducted in the AEDC-VKF Tunnel C

Abstract

Tests were conducted in the AEDC-VKF Hypersonic Wind Tunnel C to obtain pressure measurements on the tunnel nozzle wall and surface static pressures and pitot pressure on a 5-deg cone model with either a sharp or a blunt (r sub n = O.375 in.) nose. The pressure measurements were obtained to provide comparative data for laser scattering measurements of the temperature and number density of both the tunnel free-stream and the leeside of the 5-deg cone. The test was conducted at Mach number 10 with the tunnel stagnation pressure and temperature varying from 400 to 1480 psia and 750 R to 2160 R, respectively. The tunnel dew point (frost point) varied from 394 R to 476 R. A test description is presented.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1978
Accession Number
ADA060224

Entities

People

  • David H. Fikes
  • Kenneth W. Nutt

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms
  • Space

DTIC Thesaurus Topics

  • Accuracy
  • Acquisition
  • Air Force
  • Data Acquisition
  • Data Reduction
  • Dew Point
  • Dynamic Pressure
  • Free Stream
  • Mach Number
  • Measurement
  • Nomenclature
  • Pressure Measurement
  • Research Facilities
  • Static Pressure
  • Test Facilities
  • Uncertainty
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Directed Energy
  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow