Quiet-flow ludwieg tube for hypersonic transition research

Juliano T. J., Schneider S. P., Aradağ Çelebioğl S., Knight D.

AIAA Journal, vol.46, no.7, pp.1757-1763, 2008 (SCI-Expanded) identifier identifier

  • Publication Type: Article / Article
  • Volume: 46 Issue: 7
  • Publication Date: 2008
  • Doi Number: 10.2514/1.34640
  • Journal Name: AIAA Journal
  • Journal Indexes: Science Citation Index Expanded (SCI-EXPANDED), Scopus
  • Page Numbers: pp.1757-1763
  • TED University Affiliated: No

Abstract

Nearly all hypersonic tunnels have turbulent nozzle-wall boundary layers that radiate acoustic noise, generating high freestream noise levels that are an order of magnitude above flight levels. A new Mach-6 quiet tunnel has been developed to provide quiet flow at high Reynolds number with low noise levels, comparable with flight. Laminar nozzle-wall boundary layers and the resulting quiet flow have now been achieved to high Reynolds numbers of 3.5 × 106/ft (11 × 106/m), after five years of shakedown. The Mach-6 quiet tunnel is the first operational hypersonic quiet tunnel with low operating costs and good optical access.