Aero-thermal analysis of lifting body configurations in hypersonic flow

Kumar, Sachin; Mahulikar, Shripad P.

doi:10.1016/j.actaastro.2016.05.011

Cited by 27 publications

(3 citation statements)

References 26 publications

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“…In general, it is challenging for existing schemes to produce satisfactory heating profiles on sphere [ 87 ]. Therefore, in order to show the E-AUSMPW scheme’s performance in hypersonic flow’s computations, Qu conducted hypersonic flow’s computation over a blunt cone [ 88 ]. Figure 12 shows the model and the computational mesh.…”

Section: Improvements Of the Traditional Riemann Solvers For The Shock Anomalymentioning

confidence: 99%

A Review of Riemann Solvers for Hypersonic Flows

Sun

Liu

et al. 2021

Arch Computat Methods Eng

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In the design of the hypersonic airliner which can greatly shorten the flight time and conduct space travel, it is of great significance for a Riemann solver to accurately simulate hypersonic flows. In this survey, the research process on the Riemann solver for hypersonic flows is reviewed, including the constructions of the traditional Riemann solvers, improvements of the traditional Riemann solvers for the shock anomaly, and the importance of the all-speed Riemann solver for hypersonic flows. Moreover, constructions and applications of the all-speed Riemann solvers are presented. It is obvious that the Riemann solver should be capable of obtaining physical solutions at low speeds and be robust against shock anomaly near strong shocks at the same time in simulating hypersonic flows.

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Section: Improvements Of the Traditional Riemann Solvers For The Shock Anomalymentioning

confidence: 99%

A Review of Riemann Solvers for Hypersonic Flows

Sun

Liu

et al. 2021

Arch Computat Methods Eng

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“…A majority of the flow analysis done on the missile were done through numerical techniques using Computational Fluid Dynamics (CFD) [7] [8]. The software generates the calculations based mostly on the Reynolds Averaged Navier-Stokes (RANS) Equations.…”

Section: Literature Reviewmentioning

confidence: 99%

Aerodynamic Performance Enhancement of Supersonic 2D Missile Using ANSYS

Gaonkar¹,

Menon²,

Srinivas

2019

ujme

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Missile is a self-propelled vehicle flying at supersonic speeds. Their payloads are usually explosive and are also known as warheads. These warheads are used to destroy a pre-set target. The aim of this paper is to optimize the values of the lift and drag forces on the given missile for better aerodynamic performance, by carrying out numerical simulations over the supersonic missile by varying the angle of attack through a set of suitable boundary conditions, while keeping the Mach number of the missile as a fixed parameter. Aerodynamic performance of the missile is studied by varying the angle of attack from 0 to 12 degrees. For every angle of attack, the coefficient of lift and coefficient of drag variations were studied in detail and were compared with the existing literature survey so as to obtain the maximum value of C L /C D ratio in order to improve the efficiency. A model of the missile was designed to-scale on Space Claim and the flow analysis was done on FLUENT standalone system using ANSYS 16 workbench. The results obtained, were in the form of flow contours of parameters such as velocity, temperature, density, pressure and turbulence. Through these flow contours the maximum and minimum values of all parameters, as well as the variation in these parameters were estimated. From the numerical analysis it was found that maximum value of C L /C D ratio was 2.5 at 12 o angle of attack. It was also found that the velocity increased with increase in angle of attack and increased the efficiency. These results are advantageous upcoming to designers who aim to build aerodynamically efficient missiles.

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“…In addition, after oxidation at 1200 °C for 40 h, the thickness of the oxide layer in AlON with 8 wt.% SiC is only approximately 70 µm, while that of pure AlON is approximately 180 µm. However, with the rapid development of aircraft technology and continuous improvement of aircraft speed, higher requirements are put forward for advanced refractory materials [15][16][17][18]. When oxidation temperature is higher than 1200 °C, there are fewer relevant reports on the oxidation resistance of AlON, which can provide a meaningful reference for the application of AlON ceramics in the field of hightemperature structural materials.…”

Section: Introductionmentioning

confidence: 99%

Oxidation resistance performance of SiC-AlON ceramic composites at high temperature

Xiao

Zhao

et al. 2022

PAC

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The microstructure and oxidation behaviour of the pure AlON ceramics and 8 wt.% SiC-AlON composite were investigated at 700-1500?C. With increasing oxidation temperature, the surface morphology of two ceramics showed a change from acicular to flaky-like and then to granular features. With the addition of nanosized SiC particles, the oxidation resistance of the ceramics was remarkably enhanced above 1100?C. This is attributed to the formation of a dense oxide layer composed of Al2O3, SiO2 and mullite, which could cover the whole matrix and suppress further penetration of oxygen. Due to the dense oxide layer, the oxidation kinetics of the 8 wt.% SiC-AlON composites conformed to a parabolic law, while that of the pure AlON conformed to a linear law. After oxidation at 1500 ?C for 40 h, the weight gain of the 8 wt.% SiC-AlON composites was 3.07mg/cm2, which was only 22.5% of that of the pure AlON.

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Aero-thermal analysis of lifting body configurations in hypersonic flow

Cited by 27 publications

References 26 publications

A Review of Riemann Solvers for Hypersonic Flows

A Review of Riemann Solvers for Hypersonic Flows

Aerodynamic Performance Enhancement of Supersonic 2D Missile Using ANSYS

Oxidation resistance performance of SiC-AlON ceramic composites at high temperature

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