Comparison of Experimentally Measured and Computed Second-Mode Disturbances in Hypersonic Boundary-Layers

Abstract

Experiments were carried out in the Boeing/AFOSR Mach 6 Quiet Tunnel at Purdue University and the Sandia National Laboratories Hypersonic Wind Tunnel at Mach 5 and 8. The purpose was to measure second-mode boundary-layer instabilities on a 7 deg half-angle cone at zero angle of attack using surface pressure sensors. Second-mode waves were successfully measured at all three Mach numbers, including under both noisy and quiet conditions. The most amplified second-mode disturbance frequencies compared well to the linear Parabolized Stability Equations computed by the STABL software suite. The eigenfunctions are also reported, to aid in the development of new instrumentation methods. The e(expn N) method is used in an attempt to determine the N factor for transition onset prediction in both tunnels.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 2010
Accession Number
ADA572326

Entities

People

  • Christopher R. Alba
  • Katya M. Casper
  • Steven J. Beresh
  • Steven P. Schneider

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Sensors

DTIC Thesaurus Topics

  • Acquisition
  • Boundaries
  • Boundary Layer
  • Data Acquisition
  • Electrical Solitons
  • Flow
  • Frequency
  • Heat Flux
  • Hot Wire
  • Hypersonic Wind Tunnels
  • Instrumentation
  • Layers
  • Mach Number
  • Measurement
  • Reynolds Number
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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