Gasdynamic design of a two-dimensional supersonic inlet with the increased flow rate factor

Gounko, Yu. P.; Mazhul, I. I.

doi:10.1134/s086986431203002x

Cited by 10 publications

(2 citation statements)

References 4 publications

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“…The good agreements of using the SST model to predict the supersonic flow in the configurations such as inlets and isolators have been obtained by many other researchers as saw in reference papers [20], [21], [22], [23] and [24] recently. In section 3, the numbers of structured grid points for the cases are around 0.5 million and in section 4, the grid nodes are about 1 million, y plus of all the cases is under 10.…”

Section: Computational Setupmentioning

confidence: 94%

Numerical investigation on shock train control and applications in a scramjet engine

Xing

Ruan

Huang

et al. 2017

Aerospace Science and Technology

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Section: Computational Setupmentioning

confidence: 94%

Numerical investigation on shock train control and applications in a scramjet engine

Xing

Ruan

Huang

et al. 2017

Aerospace Science and Technology

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“…In order to compromise between these objectives, several geometries were investigated. Some examples are represented by multiple ramps [4][5][6], three-dimensional bumps [7], combinations of ramps and cone [8], combinations of wedges and smooth ramps [9].…”

Section: Introductionmentioning

confidence: 99%

Control of a Supersonic Inlet in Off-Design Conditions with Plasma Actuators and Bleed

Ferrero

2020

Aerospace

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Supersonic inlets are a key component of present and future air-breathing propulsion systems for high-speed flight. The inlet design is challenging because of several phenomena that must be taken under control: shock waves, boundary layer separation and unsteadiness. Furthermore, the intensity of these phenomena is strongly influenced by the working conditions and so active control systems can be particularly useful in off-design conditions. In this work, a mixed compression supersonic inlet with a double wedge ramp is considered. The flow field was numerically investigated at different values of Mach number. The simulations show that large separations appear at the higher Mach numbers on both the upper and lower walls of the duct. In order to improve the performances of the inlet two different control strategies were investigated: plasma actuators and bleed. Different locations of the plasma actuator are considered in order to also apply this technology to configurations with a diverter which prevents boundary layer ingestion. The potential of the proposed solutions is investigated in terms of total pressure recovery, flow distortion and power consumption.

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Exergy method for estimating the ramjet specific impulse

Latypov

2013

Thermophys. Aeromech.

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Gasdynamic design of a two-dimensional supersonic inlet with the increased flow rate factor

Cited by 10 publications

References 4 publications

Numerical investigation on shock train control and applications in a scramjet engine

Numerical investigation on shock train control and applications in a scramjet engine

Control of a Supersonic Inlet in Off-Design Conditions with Plasma Actuators and Bleed

Exergy method for estimating the ramjet specific impulse

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