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)


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.


Transonic Flow Nozzle Wall Supersonic Nozzle Wall Boundary Layer Favorable Pressure Gradient 
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  1. 1.
    Pate, S. R. and Scheuler, C. J., “Radiated Aerodynamic Noise Effects on Boundary-Layer Transition in Supersonic and Hypersonic Wind Tunnels”, AIAA Journal. Vol. 7, No. 3, March 1969, pp. 450–457. Also, AEDC-TR-67–236, March 1968.ADSCrossRefGoogle Scholar
  2. 2.
    Laufer, J., “Aerodynamic Noise in Supersonic Wind Tunnels”, J. Aero. Sci. Vol. 28, No. 9, Sept. 1961, pp. 685–692.MATHGoogle Scholar
  3. 3.
    Chen F. J., Malik, M. R., and Beckwith, I. E., “Instabilities and Transition in the Wall Boundary Layers of Low Disturbance Supersonic Nozzles”, AIAA Paper No. 85–1573, 1985.Google Scholar
  4. 4.
    Chen, F.-J., Malik, M. R., and Beckwith, I. E., “Comparison of Boundary Layer Transition on a Cone and Flat Plate at Mach 3.5”, AIAA Paper No. 88–0411, Jan. 1988.Google Scholar
  5. 5.
    Beckwith, I. E., Malik, M. R., and Chen, F.-J., “Nozzle Optimization Study for Quiet Supersonic Wind Tunnels”, presented at the AIAA 17th Fluid Dynamics, Plasmadynamics, and Lasers Converence, Snowmass, Colorado, June 25–27, 1984, AIAA Paper No. 84–1628.Google Scholar
  6. 6.
    Beckwith, I. E., Chen, F.-J., and Creel, T. R., Jr., “Design Requirements for the NASA Langley Supersonic Low- Disturbance Wind Tunnel”, AIAA Paper No. 86–0763-CP, 1986.Google Scholar
  7. 7.
    Strikwerda, J. C., “A Time-Split Difference Scheme for the Compressible Navier-Stokes Equations with Applications to Flows in Slotted Nozzles”, Parallel Computations, Academic Press, Inc., 1982, pp. 251–267.Google Scholar
  8. 8.
    Hopkins, D. F. and Hill, D. E., “Effect of Small Radius of Curvature on Transonic Flow in Axisymmetric Nozzles”, AIAA Journal. Vol. 4, No. 8, August 1966, pp. 1337–1343.ADSCrossRefGoogle Scholar
  9. 9.
    Nelms, L. T., “Design of Minimum Length Supersonic Nozzle Contour and Associated Subcontours”, Arnold Engineering Development Center, Arnold AFB, TN, AEDC-TR-68–212, 1968.Google Scholar
  10. 10.
    Beckwith, I. E. and Ridyard, H. W., “The Aerodynamic Design of High Mach Number Nozzles Utilizing Axisymmetric Flow with Application to a Nozzle of Square Test Section”, NACA Technical Note 2711, June 1952.Google Scholar
  11. 11.
    Harris, J. E. and Blanchard, D. K., “Computer Program for Solving Laminar, Transitional, or Turbulent Compressible Boundary-Layer Equations for Two-Dimensional and Axisymmetric Flow”, NASA TM-83207, February 1982.Google Scholar
  12. 12.
    Malik, M. R., “COSAL—A Black-Box Compressible Stability Analysis Code for Transition Prediction in Three- Dimensional Boundary Layers”, NASA CR-165925, May 1982.Google Scholar
  13. 13.
    Beckwith, I. E., Chen, F.-J. and Malik, M. R., “Design and Fabrication Requirements for Low-Noise Supersonic/ Hypersonic Wind Tunnels”, AIAA Paper No. 88–0143, 1988.Google Scholar

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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