INITIAL AERODYNAMIC CALIBRATION RESULTS FOR THE AEDC-PWT 16-FT SUPERSONIC TUNNEL

Abstract

INITIAL AERODYNAMIC CALIBRATION OF THE TESTING REGION OF THE PWT 16- Ft Supersonic Tunnel consisted of surveys of a 20-foot length of nozzle and test section in which the most desirable model locations occur. These surveys were obtained with an eight-foot traversing rake utilizing pitot-wedge and pitot- temperature probes. The data included isentropic-nozzle Mach number distributions both on and off the centerline, true local Mach number determined from the pitot-wedge probes, nozzle pressure recovery, and flow misalignment. These surveys were conducted at nozzle Mach numbers of 1.50, 1.60, 1.75, 2.00, 2.25, 2.50, 2.75, 3.00, 3.25, and 3.50. Results show that maximum Mach number variations over the surveyed length are +or- 0.02. The stagnation pressure recovery through the nozzle, for the range of specific humidity obtained during this program, varied from 0.993 to 0.961 at nozzle contour numbers from 1.50 to 3.50.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1962
Accession Number
AD0273527

Entities

People

  • C. L. Garner Jr.
  • J. H. Nichols
  • M. W. Davis

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms
  • Counter IED

DTIC Thesaurus Topics

  • Air Force
  • Boundaries
  • Boundary Layer
  • Boundary Layer Flow
  • Calibration
  • Flow
  • Flow Fields
  • Geometry
  • Guide Vanes
  • Mach Number
  • Orientation (Direction)
  • Pitot Tubes
  • Reynolds Number
  • Shock Waves
  • Three Dimensional
  • Tubes
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow