Contouring the nozzles producing a uniform supersonic flow or a thrust maximum in the presence of a curvilinear sonic line

DOI10.1134/S001546281202010XzbMath1242.76298OpenAlexW2008805261MaRDI QIDQ431755

N. I. Tillyaeva, A. A. Krajko, K. S. P'yankov, A. N. Krajko

Publication date: 2 July 2012

Published in: Fluid Dynamics (Search for Journal in Brave)

Full work available at URL: https://doi.org/10.1134/s001546281202010x

zbMATH Keywords

}\)-characteristicsequalizing nozzle contourintersections of \(C^{+}\) or \(C^{Mach number at the nozzle exitthe most rapid flow acceleration in the case of a curvilinear sonic line

Mathematics Subject Classification ID

Supersonic flows (76J20) Flow control and optimization for compressible fluids and gas dynamics (76N25)

Related Items (2)

Conjugate problem for Lagrange multipliers and consequences for partial differential equations of mixed type ⋮ Features of a turbulent jet at high supersonic velocities

Cites Work

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• Inviscid gas flows in nozzles with a steeply converging contour
• Use of flows with straight sonic line in nozzles with corners
• Supersonic ideal-gas flow of in the throat region of a nozzle
• Effect of gas non-ideality on the performance of Laval nozzles with an abrupt constriction

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