Experimental Research of Wall Pressure Distribution and Effect of Micro Jet at Mach 1.5

Azami, Muhammad Hanafi; Faheem, Mohammed; Aabid, Abdul; Mokashi, Imran; Khan, Sher Afghan

doi:10.35940/ijrte.b1187.0782s319

Cited by 16 publications

(6 citation statements)

References 13 publications

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“…The boat tail helmets can reduce drag studied by Pathan et al, [21] and found that the aerodynamic drag reduces when the helmet shape is streamlined. Azami et al, [22] explored the experimental research of wall pressure and the effect of microjet. The base pressure variation in external and internal flows using CFD analysis is studied by Pathan et al, [23] and revealed that the internal and external suddenly expanded flows are nearly the same in the base region of the flow field.…”

Section: Fig 1 Geometry Of Conementioning

confidence: 99%

Effectiveness of Cone Angle on Surface Pressure Distribution along Slant Length of a Cone at Hypersonic Mach Numbers

Shaikh

Pathan²,

Kumar

et al. 2023

ARFMTS

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In the present study, the prime attention is to numerically simulate the surface pressure distribution over the slant length of the cone at the various Mach numbers and for the considerable range of semi-cone angles. The Computational Fluid Dynamics (CFD) analysis is used to simulate the surface pressure distribution numerically. The hypersonic Mach numbers, semi-cone angle, and various locations along the slant length of a cone are considered parameters for this research work. The Mach numbers (M) considered for the research work are 5, 7, 9, 11, 13, and 15. The cone angle (θ) from 5° to 25° is considered. The results of pressure (P/Pa) are recorded at various locations (x/L) along the slant length of the cone as 0.1 to 1. The pressure distribution results are obtained by CFD analysis and compared with the analytical results available in the literature for Mach number 5. The findings obtained by CFD analysis and analytical results show good agreement. In this investigation, it is observed that the Mach number, cone angle, and slant length of the cone are the highly influential parameters for the surface pressure distribution. The pressure distribution over the slant length of the cone increases with an increase in the Mach number and the semi-cone angle.

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Section: Fig 1 Geometry Of Conementioning

confidence: 99%

Effectiveness of Cone Angle on Surface Pressure Distribution along Slant Length of a Cone at Hypersonic Mach Numbers

Shaikh

Pathan²,

Kumar

et al. 2023

ARFMTS

View full text Add to dashboard Cite

show abstract

“…Azami et al, [16,17] studied the control of suddenly expanded flows with micro-jets, an active control using an experimental method. The experiment proves that micro-jet manages to significantly base pressure.…”

Section: Literature Reviewmentioning

confidence: 99%

Effect of Expansion Level and Relief to Shear Layer in a Suddenly Expanded Flow: A CFD Approach

Ridwan

Rosnin²,

Aabid³

et al. 2022

ARFMTS

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Computational Fluid Dynamics analysis was used to study the effect of expansion level in a suddenly expanded flow for a converging-diverging nozzle expanded to the duct of larger diameter at supersonic Mach number. Parameters include the nozzle pressure ratio (NPR), L/D ratio, and area ratio. The model of the converging-diverging (C-D) nozzle suddenly expanding into the enlarged duct with the cavity was created using the Design Modeler of ANSYS Fluent. The Mach number of the study is 1.6. The area ratio varied from 2.25 to 5.29, and the L/D ranged from 1 to 10. The simulated nozzle pressure ratio (NPR) ranged from 2, 3, 4.25, and 6.375. The outcome demonstrated that the geometric alteration and NPR strongly affect the base pressure. The ambient pressure influences result in lower L/Ds. The cavity of aspect ratio 1 is most effective in raising the base pressure. Increasing the width does not yield any desirable results. However, the location of the cavity played a very significant role in base pressure regulation. The duct's wall pressure and the flow field remained identical with and without control.

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“…Whenever the control mechanism is employed, either passive or active, it is mandatory on the part of the researcher to monitor the static pressure at the duct surface and flow field in a suddenly expanded duct. The wall pressure distribution has been reported for different Mach numbers [10][11][12][13][14]. The primary observation of wall pressure is based on the Mach number variation and area ratio in their reviews.…”

Section: Literature Reviewmentioning

confidence: 99%

Studies on Flows Development in a Suddenly Expanded Circular Duct at Supersonic Mach Numbers

Aabid¹,

Khan²

2021

IJHT

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This article focuses on the flow development and the static wall pressure distribution along the circular duct from the convergent-divergent (CD) nozzle. The study aims to examine the quality of the stream in the conduit when the control is employed. The microjets are activated at the base at (PCD) of 13 mm, and the diameter of the microjets is 1 mm. Mach numbers of the investigation are 1.3, 1.9, and 2.4. The length of the duct considered was from L = 10D to 1D. The diameter of the enlarged tube was 16 mm. The experiments were conducted for NPRs from 3 to 11. The results revealed that the lowest duct length mandatory for the flow continued to attach with the circular duct wall are L/D = 1, 2, and 3 for Mach numbers 1.3, 1.9, and 2.4, respectively. The investigation outcome indicates that there are mild oscillations in the flow-field for correctly expanded flows. The oscillatory trend has a pronounced impact on the duct's flow when the jets are operated at higher NPRs. The control does not adversely affect the flow field, and the magnitude of wall pressure is nearly similar.

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Experimental Research of Wall Pressure Distribution and Effect of Micro Jet at Mach 1.5

Cited by 16 publications

References 13 publications

Effectiveness of Cone Angle on Surface Pressure Distribution along Slant Length of a Cone at Hypersonic Mach Numbers

Effectiveness of Cone Angle on Surface Pressure Distribution along Slant Length of a Cone at Hypersonic Mach Numbers

Effect of Expansion Level and Relief to Shear Layer in a Suddenly Expanded Flow: A CFD Approach

Studies on Flows Development in a Suddenly Expanded Circular Duct at Supersonic Mach Numbers

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