Three-Dimensional Supersonic Minimum Length Nozzle Design at High Temperature for Arbitrary Exit Cross Section

Abada, Omar; Zebbiche, Toufik; El-Hirtsi, Ahmed Abdallah

doi:10.1007/s13369-014-1377-z

Cited by 10 publications

(13 citation statements)

References 8 publications

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“…For the PG model (1)(2)(3) , the design data are M E and γ of gas. For the HT model (8)(9)(10)14) , the design data are M E , T 0 and C P (T) of gas. While for our RG model, the design data are extended to M E , T 0 , P 0 and C P (T, ρ) of gas.…”

Section: (30)mentioning

confidence: 99%

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Stagnation pressure effect on the supersonic minimum length nozzle design

Zebbiche

2019

Aeronaut. j.

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The aim of this work is to develop a calculation model based on the method of characteristics making it possible to study the effect of the stagnation pressure of the combustion chamber on the 2D and axisymmetric minimum length nozzle design giving a uniform and parallel flow at the exit section. The model is based on the use of the real gas approach. The co-volume and the intermolecular interaction effect are taken into account by the use of the Berthelot state equation. The effect of molecular vibration is considered in our model to evaluate the behaviour of gas at a high temperature. In this case, the stagnation pressure and the stagnation temperature are important parameters in our model. The resolution of the algebraic equations is done by the finite difference corrector predictor algorithm. The validation of the results is controlled by the convergence of the critical section ratios calculated numerically as obtained by the theory. The mass and the thrust are evaluated to improve the efficiency of the nozzle. The comparison is made with the high temperature and perfect gas models. The application is made for air.

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Section: (30)mentioning

confidence: 99%

“…While for our RG model, the design data are extended to M E , T 0 , P 0 and C P (T, ρ) of gas. Then we can consider that the PG (3) and HT (8)(9)(10) models are special cases of our presented RG model. In other words, our RG model of MOC is a generalization of the PG and HT models.…”

Section: (30)mentioning

confidence: 99%

Stagnation pressure effect on the supersonic minimum length nozzle design

Zebbiche

2019

Aeronaut. j.

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“…1,2 The minimum length nozzle (MLN) is widely used in aerospace constructions owing to better performances compared to other existing nozzles and for the simplicity of manufacture. [3][4][5][6][7] Generally, three principal performances such as M E , C F , and C Mass are of interest. In certain cases, other nozzles' geometrical parameters are included.…”

Section: Introductionmentioning

confidence: 99%

Performance improvement of supersonic nozzles design using a high-temperature model

Hamaidia

Zebbiche

Sellam

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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The aim of this paper is to discuss the development of new contours of axisymmetric supersonic nozzles giving a uniform and parallel flow at the exit section, to improve the aerodynamic performances compared to the minimum length nozzle, by increasing the exit Mach number and the thrust coefficient, and by reduction of the nozzle's mass, while holding the same throat section between the two nozzles. The new nozzle is named the best performance nozzle. Its form contains a cylindrical central body and an external wall for the flow redress. The study is done at high temperature, lower than the dissociation threshold of the molecules. The variation of the specific heats with the temperature is considered. The design is made by the method of characteristics. The predictor-corrector algorithm is used to make the numerical resolution of the obtained nonlinear algebraic equations. The validation of results is made by the convergence of the numerical critical sections ratio with that given by the theory. The comparison of the results is made with the minimum length nozzle since it is currently used in the aerospace propulsion. The design depends on M E, T0, y body, y*, and the mesh generation. The application is done with air. A computational fluid dynamics verification for the under nozzle expressed regime has shown that a flow separation with the wall is observed because of the side-loads, which are reduced for this new nozzle compared to the minimum length nozzle.

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“…1,2 Over the past five decades, much efforts have been devoted to developing different kinds of effective nozzles based on the method of characteristics (MOC), since the early work focused on two-dimensional or axisymmetric maximum thrust nozzle within a given length 3,4 and minimum length nozzle (MLN). [5][6][7] Concerning the three-dimensional nozzle design, Abada et al 8 designed a three-dimensional MLN at high temperature for arbitrary exit cross section.…”

Section: Introductionmentioning

confidence: 99%

“…5–7 Concerning the three-dimensional nozzle design, Abada et al. 8 designed a three-dimensional MLN at high temperature for arbitrary exit cross section. Mo et al.…”

Section: Introductionmentioning

confidence: 99%

Design and optimization of three-dimensional supersonic asymmetric truncated nozzle

Zhu

Zhang

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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Three-dimensional supersonic nozzle is an important component of air-breathing hypersonic vehicles to produce thrust and lift force. Since the length of nozzle with ideal design is too long to meet the trim requirements of integrated airbreathing hypersonic vehicles, it is necessary to design a truncated nozzle to provide excellent aerodynamic performance. In the present study, an axisymmetric minimum length nozzle was firstly designed using method of characteristics. Then, streamlines trace technique with an offset circular entrance was adopted to extract the three-dimensional asymmetric nozzle. Nonlinear compression method was applied to compress the nozzle to a suitable length. Afterward, a surrogate-based optimization of three design variables, namely pressure ratio of nozzle's exhaust to ambient, reserved initial expansion ratio, and average compression ratio was performed with the objectives of thrust and lift force, and a Pareto optimal front was therefore obtained. Numerical simulations were also made at six selected Pareto front cases to offer an insight into the flow fields. An infection point was observed in the Pareto front due to the maximum constrained length. The pressure ratio was found to be the most influential parameter, and the middle parts of Pareto front revealed better uniformity of exit flow.

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Three-Dimensional Supersonic Minimum Length Nozzle Design at High Temperature for Arbitrary Exit Cross Section

Cited by 10 publications

References 8 publications

Stagnation pressure effect on the supersonic minimum length nozzle design

Stagnation pressure effect on the supersonic minimum length nozzle design

Performance improvement of supersonic nozzles design using a high-temperature model

Design and optimization of three-dimensional supersonic asymmetric truncated nozzle

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