Numerical simulation and parametric study of a supersonic intake

Soltani, Mohammad Reza; Sepahi-Younsi, Javad; Farahani, Mohammad; Masoud, Afshin

doi:10.1177/0954410012436620

Cited by 22 publications

(17 citation statements)

References 14 publications

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“…It is worth emphasizing that variations of ow distortion with Mach number are a function of di user shape and can be quite di erent for various inlets. It is noted that these ndings for mixed compression inlet in the supercritical operating condition are consistent with the study done by Soltani et al [31] for external compression inlet under the similar operating condition.…”

Section: E Ects Of Free-stream Mach Numbersupporting

confidence: 81%

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Numerical Investigation of Back Pressure and Free-stream Effects on a Mixed Compression Inlet Performance

Ebrahimi

Chavoshi

2017

Scientia Iranica

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Abstract. Inlet performance has an important role in the operation of air-breathing propulsion systems. In this study, performance of a supersonic axisymmetric mixedcompression inlet in the supercritical operating condition is numerically studied. The e ects of free-stream Mach number and engine-face pressure on performance parameters, including mass ow ratio, drag coe cient, total pressure recovery, and ow distortion, are investigated. For this sake, a multi-block density-based nite volume CFD code is developed, and Reynolds-averaged Navier-Stokes equations with Spalart-Allmaras oneequation turbulence model are employed. The code is validated by comparing numerical results against other computational results and experimental data for two test cases of inviscid ow in a two-dimensional mixed-compression inlet and ow in an external compression inlet. Finally, the code is utilized for the investigation of a speci c supersonic mixed-compression inlet with the design Mach number of 2.0 and length-to-diameter ratio of 3.4. Results revealed that the increment of free-stream Mach number leads to the decrease in total pressure recovery and drag coe cient, while mass ow ratio and ow distortion increase. The e ects of engine-face pressure on performance parameters showed that by increasing the engine-face pressure, mass ow ratio and drag coe cient remain constant, while total pressure recovery increases and ow distortion decreases.

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Section: E Ects Of Free-stream Mach Numbersupporting

confidence: 81%

“…Plots of performance parameters also show a negligible di erence in the mass ow passing through the inlet. Further, drag coe cient remains nearly invariant since the mass ow passing through the inlet is constant, that is consistent with the literature [31] for the supercritical operating condition.…”

Section: Engine-face Pressure E Ectssupporting

confidence: 77%

Numerical Investigation of Back Pressure and Free-stream Effects on a Mixed Compression Inlet Performance

Ebrahimi

Chavoshi

2017

Scientia Iranica

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“…17,18 The performance of an external compression intake was investigated experimentally and numerically. 19,20 The intake was of external compression type, however, the intake in the current study is mixed compression one. In addition, in this study effect of the boundary layer suction on the intake performance is investigated.…”

Section: Introductionmentioning

confidence: 96%

Performance investigation of a supersonic air intake in the presence of the boundary layer suction

Soltani

Sepahi-Younsi

Daliri

2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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The performance of a supersonic mixed compression air intake has been investigated experimentally. The intake is of axisymmetric one and has been designed for a free stream Mach number of 2.0. The present work has two main goals, first to investigate the performance of the intake without boundary layer bleed at design and at off-design conditions and second to study the effects of a bleed slot on the intake performance. The intake has been tested at free stream Mach numbers of 1.8, 2.0, and 2.2 and at zero degrees angle of attack. Total pressure recovery, mass flow ratio, and flow distortion have been selected to assess the intake performance. The bleed slot is located upstream of the intake throat perpendicular to the compression ramp surface. The suction is applied by the natural pressure difference between the entrance and the exit faces of the bleed duct. Results show that applying the boundary layer suction upstream of the intake throat can considerably improve the intake performance at its design and off-design conditions while it does not affect the intake mass flow rate.

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“…The oscillation of this bow shock is a decisive factor in the performance of a supersonic inlet, as its oscillation, called`buzz,' has several detrimental e ects on the performance of the propulsion systems [15]. In addition, a compression wave is formed right at the cowl lip that coalesces with the bow shock downstream.…”

Section: Shadowgraphs Of Ogive and Inlet Modelsmentioning

confidence: 99%

Experimental Investigation of Shock Waves Formation and Development Process in Transonic Flow

Farahani

Jaberi

2017

Scientia Iranica

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Abstract. An extensive experimental investigation was performed to explore the shock waves formation and development process in transonic ow. Shadowgraph visualization technique was employed to provide visual description of the ow eld features. Based on the visualization, the formation process was categorized into two intrinsically di erent phases, namely, subsonic and supersonic. The characteristics of subsonic phase are well known; however, those of the supersonic one are far less studied. The supersonic phase itself is made up of two consecutive phases, namely, approaching and sweeping. The e ects of each phase on the ow eld characteristics and on shaping the supersonic regime were studied in details. In order to generalize the results, three di erent models were tested. A special terminology is suggested by authors to ease the process description and pave a way for future studies. Above all, as the transition from transonic regime to the supersonic one is a vague concept in terms of physical reasoning, a new explanation is proposed that can be used as a criterion for distinguishing between transonic and supersonic regimes.

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Numerical simulation and parametric study of a supersonic intake

Cited by 22 publications

References 14 publications

Numerical Investigation of Back Pressure and Free-stream Effects on a Mixed Compression Inlet Performance

Numerical Investigation of Back Pressure and Free-stream Effects on a Mixed Compression Inlet Performance

Performance investigation of a supersonic air intake in the presence of the boundary layer suction

Experimental Investigation of Shock Waves Formation and Development Process in Transonic Flow

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