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Thrust nozzle optimization including boundary-layer effects

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Abstract

An optimization analysis employing the calculus of variations and a numerical relaxation scheme for applying the results are presented for the design of axisymmetric, maximumthrust nozzle contours including boundary-layer effects. The method is illustrated by comparison with a known solution without boundary-layer effects. A parametric study of boundary-layer effects for a range of parameters typical of scramjet thrust nozzles is presented.

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Author information

Authors and Affiliations

  1. Purdue University, Lafayette, Indiana

    J. D. Hoffman (Associate Professor of Mechanical Engineering) & H. D. Thompson (Associate Professor of Mechanical Engineering)

  2. University of Idaho, Moscow, Idaho

    M. P. Scofield (Assistant Professor of Mechanical Engineering)

Authors
  1. J. D. Hoffman
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  2. M. P. Scofield
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  3. H. D. Thompson
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Additional information

Communicated by K. G. Guderley

This work was sponsored by the Air Force Aero-Propulsion Laboratory, Wright-Patterson Air Force Base, Ohio, under Contract No. F33615-67-C-1068.

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Hoffman, J.D., Scofield, M.P. & Thompson, H.D. Thrust nozzle optimization including boundary-layer effects. J Optim Theory Appl 10, 133–159 (1972). https://doi.org/10.1007/BF00934730

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  • DOI: https://doi.org/10.1007/BF00934730

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