Design of Minimum Length Supersonic Nozzle using the Method of Characteristics

Mishra, Nirmith Kumar; Kumar, Arun; Ganesh, Mirishkar Sai; Alam, M.A.

doi:10.35940/ijitee.b6183.129219

Cited by 5 publications

(3 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Before starting with the discussion of the results, it is important to underline that a two-dimensional MoC produces a wedge-shaped nozzle with a rectangular outlet [31]. Additionally, the nozzles produced with the twodimensional algorithm are calculated for a unit breadth and unit throat height.…”

Section: Resultsmentioning

confidence: 99%

See 1 more Smart Citation

A shape design optimization methodology based on the method of characteristics for rocket nozzles

2023

View full text Add to dashboard Cite

Even though shape optimization is a powerful tool for designing aerospace vehicles, it can be time-consuming when high-fidelity models are employed. Thus, lower-fidelity simulations covering a wider design space can be a solution for shape optimization in the early design phases. With this in mind, the present work aims to develop a low-fidelity and fast method to conduct nozzle shape optimization. This method consists in using the free-form deformation (FFD) parameterization technique to control the nozzle shape by means of an optimization algorithm to maximize the coefficient of thrust determined by a two-dimensional method of characteristics (MoC). To verify the reliability of the proposed method, a similar optimization process is carried out, recurring to high-fidelity simulations, namely using an Euler solver, in the open-source framework $$\text {SU}^2$$ SU 2 . This latter optimization process is established as a surrogate-based optimization (SBO) not only to mitigate the $$\text {SU}^2$$ SU 2 framework limitations in performing shape optimization on nozzles, but also as a way to reduce the computational power. A good agreement between the results from both methods is achieved, displaying solely a small offset concerning the optimal contour width and the coefficient of thrust. Hence, this proves the usefulness of the developed shape optimization strategy based on the MoC for the preliminary design of nozzles.

show abstract

Section: Resultsmentioning

confidence: 99%

“…In [17] and [18], Asha et al presented a study about the design of a nozzle with a minimum length using the method of characteristics (MoC). As a conclusion, both articles recommend the MoC as the most appropriate to be used for this supersonic nozzle design.…”

Section: Introductionmentioning

confidence: 99%

A shape design optimization methodology based on the method of characteristics for rocket nozzles

2023

View full text Add to dashboard Cite

show abstract

“…According to Murnaghan, 1 several conditions are shown to assort the nozzle flow: In the case of under-expanded nozzles, the pressure of the flow out of the nozzle is greater than atmospheric pressure. The expansion of the gases continues outside and the overpressure contributes to thrust.…”

Section: Introductionmentioning

confidence: 99%

Study of fluid-dynamic behavior in a convergent–divergent nozzle by shape optimization using evolutionary strategies algorithms

Bahamon,

Martinez

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

The performance and thrust of a rocket propulsion system are based mainly on the utilization of the enthalpy of the propellants in the combustion chamber. This accumulated energy is transformed into kinetic energy by the expansion and acceleration of the gases produced by the chemical reaction of combustion, using a device known as a nozzle. This project studies the aerodynamic profile to trace the wall contour of a C-D nozzle based on the technical operating conditions of a rocket engine. The wall contour is traced using different design methods and, for each nozzle section, the behavior of the fluid-thermal properties of the flow field along the flow trajectory of the aerospace nozzle is analyzed. This is necessary because, in each wall contour suggested by the models, the angle of inclination of the curvature is different (the concavity or shape of the curve changes) and, therefore, the physical magnitudes of the properties vary according to the contour. To determine which design complies with the concept that processes occurring within a nozzle are isentropic and reversible, a statistical analysis of data dispersion is performed to choose the design with the lowest energy losses as a function of friction and entropy. An unconstrained optimization is applied to maximize or minimize the cross-sectional area of the nozzle geometric profile through genetic algorithms. To corroborate the nozzle wall contour and the design methodology used, a simulation is performed to evaluate the similarities between the operating characteristics and Mach number with another nozzle of a J-2 rocket engine.

show abstract

CFD investigation of rocket exhaust thrust vector control using gas injection

Sai,

Manideep

2023

Proceedings of the 1st International Conference on Frontier of Digital Technology Towards a Sustainable Society

View full text Add to dashboard Cite

Design of Minimum Length Supersonic Nozzle using the Method of Characteristics

Cited by 5 publications

References 0 publications

A shape design optimization methodology based on the method of characteristics for rocket nozzles

A shape design optimization methodology based on the method of characteristics for rocket nozzles

Study of fluid-dynamic behavior in a convergent–divergent nozzle by shape optimization using evolutionary strategies algorithms

CFD investigation of rocket exhaust thrust vector control using gas injection

Contact Info

Product

Resources

About