Aerothermodynamic considerations for energy deposition based drag reduction technique

Desai, Siddesh; Kulkarni, Vinayak; Gadgil, Hrishikesh; John, Bibin

doi:10.1016/j.applthermaleng.2017.04.114

Cited by 18 publications

(5 citation statements)

References 13 publications

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“…Two types of finite volume based two-dimensional simulations are performed for R-SWBLI under laminar flow assumption. Perfect gas solver 21,23,24 is used for low enthalpy simulations while nonequilibrium flow solver 25–27 is employed for high enthalpy condition only. Conventional Navier–Stokes equations are solved for perfect gas flow simulations.…”

Section: Numerical Methodologymentioning

confidence: 99%

Separation mitigation using pressure feedback technique for hypersonic shock wave boundary layer interaction

Desai

Kulkarni

Gadgil

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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Present studies are focused on the use of pressure feedback technique as a separation control technique for ramp induced flow separation at hypersonic speed. Numerical simulations portrayed that though pressure feedback technique can reduce the flow separation, further cooling of the feedback channel enhances its potential for separation control. Marginal cooling of channel walls to 175 K has reduced separation bubble size by 18.18% while strong cooling of those walls to 50 K reduced the separation by 30%. Such low enthalpy perfect gas simulations also showed the lower effectiveness of pressure feedback technique with increased ramp angle. Further, it has been noticed from the perfect and nonequilibrium gas flow simulations that the cooling of pressure feedback channel introduces differential separation size for the same wall-to-total temperature ratio cases. Integration of cooled pressure feedback channel with blunt leading edge configuration showed reduced separation size for any bluntness radius. Effectiveness of this integration is seen in lowering the values of inversion and equivalent radii. Thus, use of cooled pressure feedback technique in conjunction with leading edge bluntness is not only seen to have reduced the intensity of shock wave boundary layer interaction but also has enhanced the controllability of blunted leading edge without altering the entropy layer–boundary layer interaction.

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Section: Numerical Methodologymentioning

confidence: 99%

Separation mitigation using pressure feedback technique for hypersonic shock wave boundary layer interaction

Desai

Kulkarni

Gadgil

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…For the present study, the supersonic inlet and supersonic outlet boundary conditions are used for inlet and outlet of flow computational geometry while the free‐slip boundary condition is considered for wall surfaces. The real gas solver is validated with different numerical and experimental findings as reported in the literature 30–33 . In addition, a well‐validated perfect gas 31,34,35 solver is also employed for the present investigation.…”

Section: Numerical Formulationmentioning

confidence: 99%

“…The real gas solver is validated with different numerical and experimental findings as reported in the literature. [30][31][32][33] In addition, a well-validated perfect gas 31,34,35 solver is also employed for the present investigation.…”

Section: Numerical Formulationmentioning

confidence: 99%

Shock/expansion fan interaction with real gas effects for Earth and Mars atmospheric conditions

2022

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Numerical simulations are performed to investigate the real gas effects on shock/expansion fan interaction. Initial perfect gas simulations at low enthalpy capture the flow structures efficiently and outcomes are found to have excellent agreement with the analytical calculations. Furthermore, the simulations with the real gas solver for different enthalpies showed that the variation in enthalpy significantly changes the flow structures. It is observed that an increase in enthalpy leads to a decrease and increase in the postshock and postexpansion fan Mach numbers, respectively. Another important observation is the decrement in the peak pressure ratio with an increment in the enthalpy. These effects are noted to be more pronounced for Mars's environment due to the higher dependency of specific heat on temperature.computational fluid dynamics, Earth and Martian atmospheric simulations, expansion fan, hypersonic flow, real gas flow, shock waves | INTRODUCTIONThe design of high-speed 1,2 aircraft necessitates the appropriate predictions of flow structures associated with it. These flights often encounter shocks and expansion fans. Furthermore, these shock waves and expansion fans may interact with each other. The presence of shock/ expansion fan interaction may complicate the flow structures by affecting the boundary-layer

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“…Similarly, Erdem et al [274] reported increased stagnation zone aeroheating using DC discharge device while Ohnishi et al [268] reported doubling the stagnation point heat flux values even with cold plasma devices. Based on simulations of Kulkarni et al [275,276] the flow becomes extremely hot ahead of the forebody regardless to the medium. Recently, Ganesh and John [263] predicted undesirable impact of energy devices as far as aeroheating to the forebody is concerned.…”

Section: Ac Electric Discharge 31%mentioning

confidence: 99%

“…With laserbased energy devices, effectiveness is found sensitive to laser detailed parameters [268]. In addition, increasing the energy source size for a given distance yields more aeroheating reduction but less drag reduction [239,275]. Device effectiveness can be maximized if the energy source size (relative to that of the forebody) is made as small as possible [264,275,283].…”

Section: Factors Controlling the Energy Deposition Devices Effectivenessmentioning

confidence: 99%

Forebody shock control devices for drag and aero-heating reduction: A comprehensive survey with a practical perspective

Ahmed

Qin

2020

Progress in Aerospace Sciences

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One key feature that distinguishes the flowfield around vehicles flying in supersonic and hypersonic regimes is the bow shock wave ahead of forebody. The severe drag and aeroheating impacting these vehicles can be significantly reduced if the bow shock wave ahead of the vehicles forebodies is controlled to yield weaker system of oblique shocks. Benefits of forebody shock control include increasing flight ranges, economizing fuel consumption, reducing dead weights, and thermally protecting forebody structure and onboard equipment. Forebody shock control that has been widely studied since the early 1900s is achievable in numerous techniques that vary according to the mechanism of control. While some of these techniques have already been implemented in real systems, other techniques involve serious complications and tough trade-offs. The present paper is intended to serve as the first comprehensive survey on the field of forebody shock control devices. The objectives of the present paper are multifold. The paper categorizes the various forebody shock control devices in a physics-based manner, explains the underlying physics for each device, and surveys the key studies and state-of-the-art knowledge. The paper also addresses the existing gaps in knowledge, highlights the existing systems implementing these devices, and discusses the associated practical implementation issues and design-tradeoffs. 2. Structural devices, the mechanical spikes: 2.1. Principle of operation of mechanical spikes Drag and Aeroheating Reduction Devices Fluidic Devices Opposing jets Structural Devices Mechanical spikes Energetic Devices Energy deposition Basic devices Structural-Fluidic Devices Structural-Energetic Devices Hybrid devices

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Aerothermodynamic considerations for energy deposition based drag reduction technique

Cited by 18 publications

References 13 publications

Separation mitigation using pressure feedback technique for hypersonic shock wave boundary layer interaction

Separation mitigation using pressure feedback technique for hypersonic shock wave boundary layer interaction

Shock/expansion fan interaction with real gas effects for Earth and Mars atmospheric conditions

Forebody shock control devices for drag and aero-heating reduction: A comprehensive survey with a practical perspective

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