The effect of coolant injection from the tip of spike on aerodynamic heating of nose cone at supersonic flow

Pish, F.; Moradi, Rasoul; Edalatpour, Amirhossein; Gerdroodbary, M. Barzegar

doi:10.1016/j.actaastro.2018.10.021

Cited by 81 publications

(13 citation statements)

References 49 publications

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“…In [311], they applied the same concept on a reentry capsule model. The same work was replicated numerically by Qu et al [312] whereas Pish et al [313] reported the same conclusions in their numerical study on different jet settings. Contradicting conclusions were reported by Huang et al [314] in their numerical simulation studies.…”

Section: Structural-fluidic Devicesmentioning

confidence: 52%

“…Due to the lack of experimental database, some simulation studies used experiments on isolated spikes, conventional opposing jets, or even plain blunt forebodies [314][315][316][317]328] to validate simulation techniques. Other simulation studies did not include any validation with experiments at all [313,314,323,324,329]. Hence, more experiments on this hybrid device must be conducted.…”

Section: Comments On Structural-fluidic Devicesmentioning

confidence: 99%

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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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Section: Structural-fluidic Devicesmentioning

confidence: 52%

Section: Comments On Structural-fluidic Devicesmentioning

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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“…5 The gas injection jet spike is extensively studied to tackle the aerodynamic heating problems in the high-speed flows by using air, He and CO 2 and also used in the investigation of the effect of multi air air-fuel jets on the mixing performances of the hydrogen jets within the scramjet combustor. [6][7][8][9] The gas injection-based jet spike is also found to be working similarly like the physical aerospike. [10][11][12] Another technique proposed to reduce the wave drag in hypersonic flow is the steady upstream energy addition.…”

Section: Introductionmentioning

confidence: 82%

A numerical study on the single pulsed energy addition based unsteady wave drag reduction at varied hypersonic flow regimes

Rao

John

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this study, unsteady wave drag reduction in hypersonic flowfield using pulsed energy addition is numerically investigated. A single energy pulse is considered to analyze the time-averaged drag reduction/pulse. The blast wave creation, translation and its interaction with shock layer are studied. As the wave drag depends only on the inviscid aspects of the flowfield, Euler part of a well-established compressible flow Navier-Stokes solver USHAS (Unstructured Solver for Hypersonic Aerothermodynamics) is employed for the present study. To explore the feasibility of pulsed energy addition in reducing the wave drag at different flight conditions, flight Mach numbers of 5.75, 6.9 and 8.0 are chosen for the study. An [Formula: see text] apex angle blunt cone model is considered to be placed in such hypersonic streams, and steady-state drag and unsteady drag reductions are computed. The simulation results indicate that drag of the blunt-body can be reduced below the steady-state drag for a significant period of energy bubble-shock layer interaction, and the corresponding propulsive energy savings can be up to 9%. For energy pulse of magnitude 100mJ deposited to a spherical region of 2 mm radius, located 50 mm upstream of the blunt-body offered a maximum percentage of wave drag reduction in the case of Mach 8.0 flowfield. Two different flow features are found to be responsible for the drag reduction, one is the low-density core of the blast wave and the second one is the baroclinic vortex created due to the plasma energy bubble-shock layer interaction. For the same freestream stagnation conditions, these two flow features are noted to be very predominant in the case of high Mach number flow in comparison to Mach 5.75 and 6.9 cases. However, the ratio of energy saved to the energy consumed is noted as a maximum for the lower Mach number case.

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“…Therefore, instead of using vaporized water, different gases (He, H 2 , CO 2 and N 2 ) were used to investigate the reduction of drag [10,22]. Helium (He) is found to have better performance for drag reduction as it is lighter and inert gas (as compared to CO 2 and N 2 ) [23]. Although H 2 is lightest, its reactive property can cause increase in heat transfer to the body [24].…”

Section: Introductionmentioning

confidence: 99%

Shock Reduction through Opposing Jets—Aerodynamic Performance and Flight Stability Perspectives

et al. 2019

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In this research paper, investigations of counter flow (opposing) jet on the aerodynamic performance, and flight stability characteristics of an airfoil with blunt leading-edge in supersonic regime are performed. Unsteady Reynolds-Averaged Navier-Stokes ( U R A N S ) based solver is used to model the flow field. The effect of angle of attack ( α ), free-stream Mach number ( M ∞ ), and pressure ratio ( P R ) on aerodynamic performance of airfoil with and without jet are compared. The results indicate that the opposing jet reduces drag from 30 % to 70 % , improves the maximum lift-to-drag ratio from 2.5 to 4.0, and increases shock stand-off distance from 15 % to 35 % depending on flow conditions. The effect of opposing jet on longitudinal flight stability characteristics, studied for the first time, indicate improvement in dynamic stability coefficients ( C m q + C m α ˙ ) at low angles of attack. It is concluded that the opposing jet can help mitigate flight disturbances in supersonic regime.

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The effect of coolant injection from the tip of spike on aerodynamic heating of nose cone at supersonic flow

Cited by 81 publications

References 49 publications

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

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

A numerical study on the single pulsed energy addition based unsteady wave drag reduction at varied hypersonic flow regimes

Shock Reduction through Opposing Jets—Aerodynamic Performance and Flight Stability Perspectives

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