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On the Design of a New MACH 3.5 Quiet Nozzle

  • Fang-Jenq Chen
  • Mujeeb R. Malik
  • Ivan E. Beckwith
Conference paper
Part of the ICASE/ NASA LaRC Series book series (ICASE/NASA)

Abstract

To advance boundary-layer stability and transition research and to ultimately provide reliable predictions of transition for supersonic flight vehicles, a wind tunnel is required with very low stream disturbance levels comparable to free flight conditions. A new concept for nozzle design is presented which promises a large increase in the length of the quiet test core. The Advanced Mach 3.5 Axisymmetric Quiet Nozzle is the first prototype built to prove the new design concept. The Reynolds numbers based on the measured length of the quiet test core for this new nozzle are in excellent agreement with the theoretical predictions.

Keywords

Transonic Flow Nozzle Wall Supersonic Nozzle Wall Boundary Layer Favorable Pressure Gradient 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Springer-Verlag New York Inc. 1990

Authors and Affiliations

  • Fang-Jenq Chen
    • 1
  • Mujeeb R. Malik
    • 1
  • Ivan E. Beckwith
    • 2
  1. 1.High Technology CorporationHamptonUSA
  2. 2.NASA Langley Research CenterHamptonUSA

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