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SUPERSONIC AXISYMMETRIC NOZZLE DESIGN BY MASS FLOW TECHNIQUES UTILIZING A DIGITAL COMPUTER

W. C. Moger, D. B. Ramsay

Open publisher page 9 citations

Abstract

Abstract : This report presents a method to design the inviscid wall contour of a supersonic, axisymmetric nozzle producing uniform parallel flow at the exit. The calculation methods used are restricted to a perfect gas. The axis velocity distribution must be specified. A complete flow pattern within the nozzle is computed by the method of characteristics beginning at Mach 1.0 on the axis and extending to the region of uniform parallel flow at the exit. The wall points are calculated by means of a mass integration technique. The methods of calculation included have been programmed in Fortran II language, and a complete listing of the program is given.

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What this paper is about

Abstract : This report presents a method to design the inviscid wall contour of a supersonic, axisymmetric nozzle producing uniform parallel flow at the exit. The calculation methods used are restricted to a perfect gas. The axis velocity distribution must be specified. A complete flow pattern within the nozzle is computed by the method of characteristics beginning at Mach 1.0 on the axis and extending to the region of uniform parallel flow at the exit. The wall points are calculated by means of a mass integration technique. The methods of calculation included have been programmed in Fortran II language, and a complete listing of the program is given.

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OpenAlex reports 9 citations for this work. Citation counts describe recorded attention and do not establish research quality.

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Available abstract

Abstract : This report presents a method to design the inviscid wall contour of a supersonic, axisymmetric nozzle producing uniform parallel flow at the exit. The calculation methods used are restricted to a perfect gas. The axis velocity distribution must be specified. A complete flow pattern within the nozzle is computed by the method of characteristics beginning at Mach 1.0 on the axis and extending to the region of uniform parallel flow at the exit. The wall points are calculated by means of a mass integration technique. The methods of calculation included have been programmed in Fortran II language, and a complete listing of the program is given.

Key concepts: Nozzle, Rotational symmetry, Supersonic speed, Digital computer, Choked flow, Flow (mathematics), Computer science, Aerospace engineering

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