Tip-to-tail numerical simulation of a hypersonic air-breathing engine with ethylene fuel

Dharavath, Malsur; Manna, P.; Chakraborty, Debasis

doi:10.1016/j.actaastro.2016.07.014

Cited by 7 publications

(4 citation statements)

References 19 publications

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“…al. [17]. The plan and side view show the sweep-back angle and thickness of the vehicle, respectively.…”

Section: Methodsmentioning

confidence: 99%

“…This type of CMC has excellent thermal diffusivity which can prevent the localization of Engineering Materials and Engineering Design Fig. 4: Schematic of a typical hypersonic cruise vehicle [17] thermal loads on the leading edge tip. A carbon fibre-reinforced C-SiC (C/C-SiC) composite was used for the body of the control surface as it possesses excellent thermophysical properties and low density.…”

Section: Methodsmentioning

confidence: 99%

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Thermo-Structural Response Prediction of UHTCC Control Surface for Hypersonic Cruise Vehicle

Ghori,

Narendar,

Dubey

2023

AMM

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One of the most complex issues that govern the design of a hypersonic vehicle is aerodynamic heating which is much more severe for an air-breathing vehicle as it operates within the atmosphere for longer durations. Due to the detrimental impact of aerodynamic heating on the vehicle structure, it is imperative to develop a robust thermal protection system that can protect the vehicle from high temperatures. However, the development of sophisticated TPS for slender components is impractical and, therefore, requires a hot structure system that can operate at substantial aerothermal loads. The aim of this study is to predict the impact of aero-heating on a UHTCC-based hot structure system of a hypersonic cruise vehicle through uncoupled thermo-structural analysis of the control surface. Validation of numerical methods implemented is done through literature comparison and grid independency tests.

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“…al. [17]. The plan and side view show the sweep-back angle and thickness of the vehicle, respectively.…”

Section: Methodsmentioning

confidence: 99%

Section: Methodsmentioning

confidence: 99%

Thermo-Structural Response Prediction of UHTCC Control Surface for Hypersonic Cruise Vehicle

Ghori,

Narendar,

Dubey

2023

AMM

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“…Global mechanisms of one step reaction 12,13 or several steps of reactions with hydrogen (H 2 ) and carbon monoxide (CO) as intermediates [14][15][16] were adopted in previous combustion simulations of scramjet combustors. 6,13,[16][17][18] Due to the lack of universality of this kind of mechanisms, the prediction results gained are unsatisfactory under some circumstances, 17,19 and the relevant combustion phenomena like ame propagation and dynamic evolution of combustion processes cannot be explained reasonably. 20,21 Furthermore, they predict mostly incorrect trends or even fail to be solved in predicting fuel characteristics in kinetic simulations.…”

Section: Introductionmentioning

confidence: 99%

Application of static integrated skeletal reduction and tabulation of dynamic adaptive chemistry in the combustion simulation of ethylene-fueled scramjet combustor

Li,

Liu,

Wang

2024

RSC Adv.

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“…With the further study of hypersonic vehicles, the aerodynamic shape of the aircraft becomes more and more complex, making grid generation difficult. Therefore, researchers have focused on methods of generating meshes for complex shapes quickly and efficiently (Piscitelli et al, 2017;Dharavath et al, 2016;Rong et al, 2017& Xu et al, 2017.…”

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confidence: 99%

Assessment of Numerical Method by Experimental Data for Integrated Hypersonic Vehicles

Wen

Liu

et al. 2019

JAFM

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This paper addresses the problem of rapid aerodynamic assessment and experimental verification of integrated hypersonic vehicles. Based on the adaptive Cartesian grid system, the aerodynamic performance of the air-breathing hypersonic vehicle is evaluated. Corresponding shrunken experimental model is investigated in FL-28 transient hypersonic wind tunnel. The grid-independent validation confirmes the proposed meshing method and optimal grid parameters. The convergent method is used for the aircraft model to calculate several flight conditions in cold state, and the calculated results are compared with the wind tunnel test data. The results show that in order to validate the accurate non-viscous dynamic characteristics of both internal and external flows, it is necessary to locally encrypt the grids of inner flow channel while ensuring the overall grid density of the aircraft. Although the computational time increases after grid encryption, the rapid prediction method of aerodynamic performance meets the requirements for engineering design. Compared with experimental results, there are several shockwave features invisible in the numerical results due to the simplification of solution procedure. The aerodynamic force coefficients obtained by the numerical method are verified by the experimental data and the same numerical method can be used in the conceptual design phase of aerodynamic shapes, which can greatly shorten the development cycle.

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Tip-to-tail numerical simulation of a hypersonic air-breathing engine with ethylene fuel

Cited by 7 publications

References 19 publications

Thermo-Structural Response Prediction of UHTCC Control Surface for Hypersonic Cruise Vehicle

Thermo-Structural Response Prediction of UHTCC Control Surface for Hypersonic Cruise Vehicle

Application of static integrated skeletal reduction and tabulation of dynamic adaptive chemistry in the combustion simulation of ethylene-fueled scramjet combustor

Assessment of Numerical Method by Experimental Data for Integrated Hypersonic Vehicles

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