Stagnation temperature effect on the supersonic axisymmetric minimum length nozzle design with application for air

Zebbiche, Toufik

doi:10.1016/j.asr.2011.08.012

Cited by 21 publications

(28 citation statements)

References 10 publications

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“…The values of M 3 and P 3 are determined analytically. Whereas for the HT model (9) , the Euler corrector algorithm contains four equations to determine x 3 , y 3 , T 3 and θ 3 . In this case, M 3 , ρ 3 and P 3 are determined analytically, and for the PG model (3) , the Euler corrector algorithm always contains four equations to determine, in this case, x 3 , y 3 , M 3 and θ 3 .…”

Section: Calculation Procedures For Internal Pointsmentioning

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: Calculation Procedures For Internal Pointsmentioning

confidence: 99%

“…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%

Stagnation pressure effect on the supersonic minimum length nozzle design

Zebbiche

2019

Aeronaut. j.

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“…The propellant fluid is modeled using the ideal gas law with constant specific heat ratios P ¼ ρRT This differs very little from real gas models in the range of temperatures and pressures used (Donaldson 1948;Zebbiche 2011). Total pressure and total temperature were set as inlet conditions.…”

Section: Two-dimensional Without Boundary Layer Modelmentioning

confidence: 99%

Planar Nozzles for Controllable Microthrusters

2017

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Orbital maneuvering of microsatellite and nanosatellite requirements can be efficiently addressed by planar nozzles, in which realtime thrust control is gained actuating on the nozzle throat area. In the present work, the method of characteristics is used to design a hypersonic contour; then, the resulting profile is laser cut, assembled, and built into a propulsion system to finally perform tests in a vacuum chamber under several working conditions. Results are used to validate the profile and modeling assumptions and investigate overall behavior. Tests showed that thrust-inlet pressure ratio is a linear function of separation between nozzle contours and that no additional losses are introduced in the system. The corresponding design/manufacture/assembly tools can be used to a provide low-cost/low-weight controllable propulsion systems to the small-satellite industry with no efficiency loss.

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“…Several methods such as different types of injectors and strut-, cavity-, and ramp-based injection systems have been offered and enhanced mixing and penetration substantially [4] and developed flow residence time [5], stagnated flow ahead of the structure effects substantial pressure losses, increases drag forces, and incites considerable local heating loads [6,7]. The majority of these studies has concentrated on a single transverse jet at a variety of conditions such as injection angles, the size of the injector and porthole shapes under different conditions of freestream and fuel injection.…”

Section: Introductionmentioning

confidence: 99%

“…Since an oxidizer tank is not required in these engines, they are preferred to rocket engines. These advantages have motivated researchers in recent years [3][4][5][6]. A successful fuel injection within the scramjet combustor is the main challenges of the scramjet.…”

Section: Introductionmentioning

confidence: 99%