Plume boundary jump of an underexpanded jet exhausting counter to a freestream.

Whitfield, David L.; Smithson, H K; Price, L. L.

doi:10.2514/3.6918

Cited by 5 publications

(7 citation statements)

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“…In this part, we would like to verify the practicalities of the numerical method. As is seen above, the simulation we have done is based on the same missile model as is shown in [2] under the condition of Ma = 1.96 and p e / p ∞ = 2.469. Figure 3 depicts the surface pressure coefficients obtained both by the simulation in this paper and the experiment quoted in [2], indicating that the numerical results of ours are in accordance with the experimental data mentioned in the corresponding reference.…”

Section: Numerical Simulation and Methods Assessmentmentioning

confidence: 99%

“…As is seen above, the simulation we have done is based on the same missile model as is shown in [2] under the condition of Ma = 1.96 and p e / p ∞ = 2.469. Figure 3 depicts the surface pressure coefficients obtained both by the simulation in this paper and the experiment quoted in [2], indicating that the numerical results of ours are in accordance with the experimental data mentioned in the corresponding reference. Figure 4 shows the structures of the flowfield obtained by both the simulation in this paper and the experimental results mentioned in [2].…”

Section: Numerical Simulation and Methods Assessmentmentioning

confidence: 99%

“…Since then, numerous experimental studies [2–11] have been done to determine the interaction between the base jet and the supersonic flow around the projectile from the 1960s to the beginning of the 21st century. For example, in 1998, Banning et al [8] did a large amount of research on the flowing characteristics of the interaction flowfield in TST-27 transonic and supersonic wind tunnel.…”

Section: Introductionmentioning

confidence: 99%

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Numerical Research of Aerodynamic Characteristic Effects of Base Jet on Supersonic Rocket

Lei

Zheng

Huang

2013

Advances in Mechanical Engineering

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Based on finite volume method, the interaction between base jet and supersonic flow around the rocket is simulated by Navier-Stokes equations with SST k-ω turbulence model and implicit algorithm. The pressure contours, the streamline patterns, and the variation of the aerodynamic characteristics of the rocket with the flying altitude, Mach number, and the angle of attack are shown and analyzed. Numerical results demonstrate that in supersonic flow, the base jet has a noticeable effect on the surface pressure of the body and the tails, leading to the decreases of the coefficients of the normal force, the pitching moment, and the pressure center. Furthermore, the higher the flying altitude, the more grave decreases of the coefficients of the normal force, the pitching moment and the pressure center. However, with the increase of Mach number, the more grave the decreases of the normal force coefficient and the pitch moment coefficient are found, while the less grave decrease is found with the pressure center coefficient. With the increase of the angle of attack, the more grave decreases are found with the coefficients of the normal force and the pitching moment, while the decrease of the pressure center coefficient remains almost the same.

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Section: Numerical Simulation and Methods Assessmentmentioning

confidence: 99%

Section: Numerical Simulation and Methods Assessmentmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Numerical Research of Aerodynamic Characteristic Effects of Base Jet on Supersonic Rocket

Lei

Zheng

Huang

2013

Advances in Mechanical Engineering

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“…Finley [140] confirmed the impact of jet temperature and specific heat ratio on heat transfer to the vehicle rather than the pressure distribution on it. 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].…”

Section: Factors Controlling the Counterflow Effectivenessmentioning

confidence: 99%

“…Figure 5a illustrates the macroscopic features of the SPM. As both and orifice area increase in the SPM, the size of the Mach cell increases in axial and lateral directions [139,[141][142][143]. This pushes the interface and the fore shock further away from the vehicle.…”

Section: Principle Of Operation Of Counterflow Jetsmentioning

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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Interaction of a sonic boundary-layer counterjet with a supersonic flow

Glagolev¹,

Panov²

1978

Fluid Dyn

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Plume boundary jump of an underexpanded jet exhausting counter to a freestream.

Cited by 5 publications

References 0 publications

Numerical Research of Aerodynamic Characteristic Effects of Base Jet on Supersonic Rocket

Numerical Research of Aerodynamic Characteristic Effects of Base Jet on Supersonic Rocket

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

Interaction of a sonic boundary-layer counterjet with a supersonic flow

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