Thermal protection performance of opposing jet generating with solid fuel

Shen, BinXian; Liu, Weiqiang

doi:10.1016/j.actaastro.2017.12.024

Cited by 21 publications

(5 citation statements)

References 17 publications

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“…178,198 But some studies mentioned that jet temperature harms the thermal protection system as heat transfer attains its peak value at the reattachment point. 199,200 In contrast, other studies show that jet temperature has no effect on shock standoff distance, and even it would not affect the drag, 199,200 whereas, latest studies revealed that an increase in jet total temperature yields more drag reduction when plasma is used as ejection material. 195…”

Section: Active Techniquesmentioning

confidence: 94%

Review of wave drag reduction techniques: Advances in active, passive, and hybrid flow control

Rashid

Nawaz

Maqsood

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Typical challenges of supersonic flight include wave drag, acoustic signature, and aerodynamic heating due to the formation of shock waves ahead of the vehicle. Efforts in the form of sleek aerodynamic designs, better propulsion systems, and the implementation of passive and active techniques are generally adopted to achieve a weaker shock wave system. Shock reduction can improve flight range, reduce fuel consumption, and provide thermal protection of the forebody region. This paper briefly reviews shock reduction techniques, including passive, active, and hybrid flow control. Airfoil shape optimization, mechanical spike, and forebody cavities are studied as passive flow control approaches. For active flow control, developments in the area of opposing jets and energy deposition are explored. The combination of active and passive flow control and the hybrid flow techniques are discussed in the end. The discussions include the principle of operation, physics of fluid behavior, and overall contribution to flight stability characteristics. The implications in the usage of these technologies, along with potential gaps, are also identified. This comprehensive review can serve as the basis for contemporary solutions to realize sustainable supersonic travel for the aviation industry.

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Section: Active Techniquesmentioning

confidence: 94%

Review of wave drag reduction techniques: Advances in active, passive, and hybrid flow control

Rashid

Nawaz

Maqsood

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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show abstract

“…Impact of jet temperature on drag reduction capabilities of opposing jet was a point of debate. The jet temperature was proved in some studies to have no impact on the fore shock standoff distance [169] nor on drag [168]. Other studies [166,170] confirmed that increasing the jet total temperature yields more drag reduction which explains the relative superiority of plasma and high-temperature jets over conventional ones [166].…”

Section: Factors Controlling the Counterflow Effectivenessmentioning

confidence: 97%

“…In contrast, it was shown that increasing the specific heat ratio pushes the fore shock further away from the body [141]. Jet temperature has a negative impact of the thermal protection capabilities of the jet as it increasing the peak heat transfer at the reattachment point [145,168,169]. Impact of jet temperature on drag reduction capabilities of opposing jet was a point of debate.…”

Section: Factors Controlling the Counterflow Effectivenessmentioning

confidence: 99%

“…A solid propellant engine was used by Ganiev et al [170] as a source for high temperature jet in their experiments. This concept was recently revisited by Shen and Liu [169]. Instead of using the real combustion gas products in their numerical simulations, they used air with corresponding temperatures.…”

Section: Design Tradeoffs and Issues Of Practical Implementation Of Omentioning

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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“…Research from [35,36] employed various combination of opposing jet with aerospike and aerodisk, and they also investigated the effect of using carbon dioxide and helium as coolant. The authors of [37][38][39] reported multiple research on the opposing jet and its combination with transpiration cooling. Zhang et al [40] launched a transient numerical investigation on a design with a centered opposing jet and a circular slot around the centered jet.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation on the Thermal Protection Characteristics of a New Active Jet Design Parameter for Hypersonic Flight Vehicle

Tian

Duan

Chen

2023

International Journal of Aerospace Engineering

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This study investigated the thermal protection performance of an active jet thermal protection system (PRsAJ-TPS) based on a new jet design parameter PRs for hypersonic flight vehicles (HFVs). The new parameter PRs is defined as the relationship between the jet flow total pressure and the free flow total pressure behind the outer bow shock. A 20° tilted nozzle design is employed together with the PRs to form the PRsAJ-TPS. Theoretical and numerical analysis is performed to prove the advantages of using the PRs. A conventional in-house CFD solver with the k ‐ ω SST turbulence model is utilized to perform the calculation. The influence of different PRs (working in the short penetration mode) and flight angles of attack on the performance of the PRsAJ-TPS is also studied. The simulation results confirmed that with a constant PRs, the Mach disk location stays the same and the normalized heat flux reduction is similar at different flight conditions. Nearly linear relationships exist between the new design parameter PRs and thermal protection performance indicators. The PRsAJ-TPS also exhibits good protection when flight angle of attack (AoA) varies between 0° and 40°, with the best results achieved at AoA = 0 ° . This study provides valuable information for the engineering application of the jet-based TPS to future HFVs.

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Thermal protection performance of opposing jet generating with solid fuel

Cited by 21 publications

References 17 publications

Review of wave drag reduction techniques: Advances in active, passive, and hybrid flow control

Review of wave drag reduction techniques: Advances in active, passive, and hybrid flow control

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

Numerical Investigation on the Thermal Protection Characteristics of a New Active Jet Design Parameter for Hypersonic Flight Vehicle

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