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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This work was sponsored by the Air Force Aero-Propulsion Laboratory, Wright-Patterson Air Force Base, Ohio, under Contract No. F33615-67-C-1068.
Communicated by K. G. Guderley
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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
- Parametric Study
- Optimization Analysis
- Relaxation Scheme
- Nozzle Contour
- Thrust Nozzle