Rapid prediction of hypersonic blunt body flows for parametric design studies

Hinman, W. Schuyler; Johansen, Craig T.

doi:10.1016/j.ast.2016.08.007

Cited by 23 publications

(6 citation statements)

References 18 publications

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“…hy2Foam is a fusion of additional physical models to incorporate thermochemical nonequilibrium with the existing solver called rhoCentralFoam, developed for compressible flows and based on the OpenFOAM framework [16]. The thermochemical nonequilibrium modelling of the solver was validated for several cases ranging from zero-dimensional chemical kinetics to multidimensional hypersonic flows [9,[17][18][19], and the Energies 2020, 13, 606 4 of 17 underlying numerics of the solver was also validated for the hypersonic cases relevant to the present study [20][21][22].…”

Section: Methodsmentioning

confidence: 99%

Numerical Analysis of Thermochemical Nonequilibrium Flows in a Model Scramjet Engine

Han

Lee

2020

Energies

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This numerical study was conducted to investigate the flow properties in a model scramjet configuration of the experiment in the T4 shock tunnel. In most numerical simulations of flows in shock tunnels, the inflow conditions in the test section are determined by assuming the thermal equilibrium of the gas. To define the inflow conditions in the test section, the numerical simulation of the nozzle flow with the given nozzle reservoir conditions from the experiment is conducted by a thermochemical nonequilibrium computational fluid dynamics (CFD) solver. Both two-dimensional (2D) and three-dimensional (3D) numerical simulations of the flow in a model scramjet were conducted without fuel injection. Simulations were performed for two types of inflow conditions: one for thermochemical nonequilibrium states obtained from the present nozzle simulation and the other for the data available using the thermal equilibrium and chemical nonequilibrium assumptions. The four results demonstrate the significance of the modelling approach for choosing between 2D or 3D, and thermal equilibrium or nonequilibrium.

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Section: Methodsmentioning

confidence: 99%

Numerical Analysis of Thermochemical Nonequilibrium Flows in a Model Scramjet Engine

Han

Lee

2020

Energies

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“…In preliminary design practice, thousands of design configurations are typically evaluated by an optimization algorithm to find the best fit [5][6][7][8][9][10]. As a consequence, a preliminary appraisal of vehicle performances is commonly performed using high-efficiency, low-order fidelity methods that give support to a multidisci-plinary analysis performed with a computational effort which fit the typical timeline of the conceptual design phase [11].…”

Section: Introductionmentioning

confidence: 99%

“….24099 9 International Journal of Aerospace Engineering methodology for a conceptual design configuration, loworder fidelity methods [3,5] are used for each subdiscipline to reduce the computational time [11].…”

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confidence: 99%

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Thermal Protection System Design of a Reusable Launch Vehicle Using Integral Soft Objects

Aprovitola

Iuspa

Viviani

2019

International Journal of Aerospace Engineering

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In the present paper, a modelling procedure of the thermal protection system designed for a conceptual Reusable Launch Vehicle is presented. A special parametric model, featuring a scalar field irradiated by a set of bidimensional soft objects, is developed and used to assign an almost arbitrary distribution of insulating materials over the vehicle surface. The model fully exploits the autoblending capability of soft objects and allows a rational distribution of thermal coating materials using a limited number of parameters. Applications to different conceptual vehicle configurations of an assigned thickness map, and material layout show the flexibility of the model. The model is finally integrated in the framework of a multidisciplinary analysis to perform a trajectory-based TPS sizing, subjected to fixed thermal constraints.

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“…In preliminary design practice, thousands of design configurations are typically evaluated by an optimization algorithm to find the best fit [5][6][7][8][9][10][11]. Therefore, a preliminary appraisal of vehicle performances is commonly performed using high-efficiency, low-order fidelity methods that give a support to a multidisciplinary analysis performed with a computational effort which fit the typical timeline of the conceptual design phase [11]. In current studies, TPS sizing is performed using several simplified assumptions, carrying out a one-dimensional heat conduction analysis with panel thickness modeled using stackups of different materials [12].…”

Section: Introductionmentioning

confidence: 99%

Parametric Integral Soft Objects-based Procedure for Thermal Protection System Modeling of Reusable Launch Vehicle

Aprovitola¹,

Iuspa²,

Viviani³

2019

Hypersonic Vehicles - Past, Present and Future Developments

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The present paper deals with a modeling procedure of a thermal protection system (TPS) designed for a conceptual reusable launch vehicle (RLV). A novel parametric model based on a scalar field created by a set of soft object primitives is used to assign an almost arbitrary seamless distribution of insulating materials over the vehicle surface. Macroaggregates of soft objects are created using suitable geometric supports allowing a distribution of coating materials using a limited number of parameters. Applications to different conceptual vehicle configurations of an assigned thickness map and materials layout show the flexibility of the model.

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Rapid prediction of hypersonic blunt body flows for parametric design studies

Cited by 23 publications

References 18 publications

Numerical Analysis of Thermochemical Nonequilibrium Flows in a Model Scramjet Engine

Numerical Analysis of Thermochemical Nonequilibrium Flows in a Model Scramjet Engine

Thermal Protection System Design of a Reusable Launch Vehicle Using Integral Soft Objects

Parametric Integral Soft Objects-based Procedure for Thermal Protection System Modeling of Reusable Launch Vehicle

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