Designing three-dimensional nozzles to achieve near-uniform supersonic or hypersonic flow in the rectangular exit section

Aukin, M. K.; Kraiko, A. N.; Lubimov, D. A.; Makarov, V. E.; Tillyaeva, N. I.

doi:10.1007/bf02079401

Cited by 1 publication

(14 citation statements)

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“…Generally the execution time for design problems is quite high despite the power of calculator used since there is repetition of calculation. The methods developed for determining the contours of the three dimensional nozzles are based on the determination of the internal stream lines using the definition of the stream function [1][2][3][4][5][6]. As the flow is considered as perfect and nonviscous, the stream lines can represent rigid surfaces and hence a wall shape of obstacles [7].…”

Section: Introductionmentioning

confidence: 99%

“…As the flow is considered as perfect and nonviscous, the stream lines can represent rigid surfaces and hence a wall shape of obstacles [7]. In our case these stream lines can represent the wall of the nozzle [1][2][3][4][5][6]. The use of these methods requires a very high computational time since the search of the points of the stream lines is based on the use of the segments in upward and downward characteristics from the developed internal mesh in the axisymmetric nozzle, which becomes impossible for fine meshes, in a time when a fine mesh give a high precision.…”

Section: Introductionmentioning

confidence: 99%

“…For a small number of N S and N P , the design becomes possible, but with moderate precision. This gives that the methods developed in references [1][2][3][4][5][6] are limited by a certain maximum of discretization. It is not necessary, in the general case, to know the properties of the flow inside the nozzle.…”

Section: Introductionmentioning

confidence: 99%

“…Only the axisymmetric nozzle contour is desired. But if the design is made as a passage for the design of the three dimensional nozzle, it is necessary to determine the internal mesh information according to references [1][2][3][4].…”

Section: Introductionmentioning

confidence: 99%

“…The reference [2] deals with the design of the three dimensional nozzles from a given axisymmetric shape taken as a second-degree polynomial for the use of the PG model, using the definition of a stream line always in an internal mesh. References [3][4] deal with the problem presented in reference [2] but only for a square section. In addition a truncation is presented in the reference [4].…”

Section: Introductionmentioning

confidence: 99%

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Rapid design method and new contours for a class of three dimensional supersonic nozzle of arbitrary exit cross section

Zebbiche

2018

Mechanics & Industry

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The aim of this work is to develop a new and rapid numerical method for designing a new contour of the supersonic nozzle with arbitrary exit cross sections as a class of three dimensional nozzle extracted from the calculation of stationary flow solutions in axisymmetric nozzle. The application is made for nozzle giving a uniform and parallel flow at the exit section. The determination of the points of the axisymmetric nozzle contours in a non-dimensional manner with respect to the arbitrary throat radius is necessary. The exit section of the nozzle must be discretized at several points. The radii of the points of the throat section are determined by equalizing the ratio of the axisymmetric critical sections corresponding to each selected point of the exit section. Each point passes a contour of the nozzle to the throat where their position is determined by the multiplication of the non-dimensional positions of the axisymmetric nozzle point by the throat radius of this contour. A uniform portion is added at the end of each contour to compensate the decrease in its length. Longitudinal discretization of the nozzle is necessary. The flow properties of each point are the same as those of the points of the axisymmetric nozzle. The temperature and the deviation of the flow at each point of any section are determined by their interpolations between two successive points of each contour. The Mach number, the pressure and the density are determined accordingly. The application is made for air at high temperature lower than the dissociation threshold of the molecules.

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Section: Introductionmentioning

confidence: 99%