DLR Cavity Pressure Oscillations, Experimental

Abstract

Wind tunnel tests were carried out with the aim of establishing a measured unsteady surface pressure data set in and around a box- shaped shallow cavity, subject to tangential flow in the transonic Mach number range. Apart from the baseline case, for which systematic Mach number and Reynolds number variations were completed, the main purpose of the tests was to investigate the effect of certain upstream mounted passive flow control devices on the cavity oscillations for selected Mach numbers. This chapter contains the description of two baseline case data sets of unsteady surface pressures for freestream Mach number M=0.8 and M=1.33 respectively made available to RTO.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 2000
Accession Number
ADP010730

Entities

People

  • Jan Delfs

Organizations

  • German Aerospace Center

Tags

Communities of Interest

  • Sensors
  • Space

DTIC Thesaurus Topics

  • Accuracy
  • Boundary Layer
  • Data Acquisition
  • Data Sets
  • Dynamic Pressure
  • Flow
  • Geometry
  • Hypervelocity Flow
  • Leading Edges
  • Mach Number
  • Measurement
  • Pressure Transducers
  • Reynolds Number
  • Static Pressure
  • Transducers
  • Turbulent Mixing
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerospace Test and Evaluation
  • Fluid Mechanics and Fluid Dynamics.