Towards High-Reynolds-Number Quiet Flow in Hypersonic Wind Tunnels

Abstract

This grant was initially focused on developing high-Reynolds-number quiet 0-ow in the Boeing/AFOSR Mach-6 Quiet Tunnel at Purdue. Reliable quiet 0-ow was achieved at freestream unit Reynolds numbers of more than 3 million per foot, beginning in Sept. 2006. The facility became the only operational hypersonic quiet tunnel, anywhere in the world. Tunnel noise was then shown to have a substantial effect on: (a) roughness-induced transition for the X-51A forebody and a slender cone, and (b) transition induced by stationary cross flow waves. Quiet-tunnel measurements were also made to aid estimates of transition for the DARPA FALCON HTV-2 program. Second-mode instability waves were measured on a slender cone using hot wires, fast pressure sensors, and ALTP heat-transfer gauges.

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Document Details

Document Type
Technical Report
Publication Date
Apr 13, 2009
Accession Number
ADA500049

Entities

People

  • Steven P. Schneider

Organizations

  • Purdue University

Tags

Communities of Interest

  • Advanced Electronics
  • Materials and Manufacturing Processes
  • Sensors

DTIC Thesaurus Topics

  • Boundary Layer
  • Detectors
  • Flow
  • Fluid Dynamics
  • Heat Transfer
  • Hot Wire
  • Hypersonic Wind Tunnels
  • Measurement
  • Pressure Measurement
  • Reynolds Number
  • Roughness
  • Stagnation Pressure
  • Stagnation Temperature
  • Surface Temperature
  • Three Dimensional
  • Tubes
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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