Analytical and Numerical Simulation of Surface Pressure of an Oscillating Wedge at Hypersonic Mach Numbers and Application of Taguchi's Method

An experimental study is presented in this paper to evaluate the enhancement of heat transfer characteristics. This includes the study of a steady air jet impinging on a planar aluminum plate with constant heat flux. Extensive industrial applications of heat transfer include electronic heat sinks, the food industry, automobiles, and heat exchangers. The magnitude of the local Nusselt number along the streamwise direction is determined through detailed experimental computation using the infrared radiometry technique. The range of Reynolds number was selected between 6500 ≤ Re ≤ 15000 and the air jet outlet-to-target surface spacing 2 ≤ Y/D ≤ 6. The objective is to develop a semi-empirical correlation that can be used to determine the distribution of local Nusselt numbers over a flat plate. Considering the objective function of the spacing between the air jet outlet and target surface spacing (Y/D), Reynolds number (Re), and non-dimensional number from stagnation point in the radial direction of the plate (r’/D), it was observed that the heat transfer rates are higher for the configuration Y/D = 4 for varying Reynolds numbers, a 5 percent increase was observed. The stagnation Nusselt number shows an increasing trend up to Y/D = 4, for Reynolds numbers 10,000 and 12,000 respectively, the corresponding stagnation Nusselt numbers are 110 and 115. In comparison to the stagnation Nusselt number, which is the same Reynolds number corresponds to, the transition field Nusselt number had heat transfer values that were 12% lower.

Section: Introductionmentioning

confidence: 89%

Experimental Investigation of Local Nusselt Profile Dissemination to Augment Heat Transfer under Air Jet Infringements for Industrial Applications

Shaikh Sohel Mohd Khalil,

Rai Sujit Nath Sahai,

Nitin Parashram Gulhane

et al. 2024

“…Using ANSYS workbench the meshing and modeling are completed and for the analysis and post-processing, ANSYS Fluent was used. To obtain the correct and precise numerical results, the structured mesh is used [31][32][33][34][35][36][37][38][39][40][41][42][43]. The Mach numbers span interval taken into the account as 5.0, 7.0, 9.0, 10.0, and 15.0 for the analysis together with semi-cone angles as 5°, 10°, 15°, 20° and 25°.…”

Section: Methodology 21 Cfd Analysismentioning

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

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.

“…The minimal duct length for the flow to stay attached is 2D for nozzle pressure ratios greater than 5, according to research on convergent-divergent nozzles utilizing microjets at Mach 2.1 [22]. Shamitha et al, [23] examined the wedge's surface pressure for a large angle of incidence at hypersonic Mach number. According to the findings, surface pressure increases as hypersonic Mach numbers and angle of incidence increase.…”

Section: Active Controlmentioning

confidence: 99%

Control of Base Pressure at Supersonic Mach Number in a Suddenly Expanded Flow

Tun Nurhanis,

Ambareen Khan,

Mohammad Nishat Akhtar

et al. 2023

In improving the efficiency of applications for flow over a blunt body like missiles and rockets, passive and active control is used to increase the base pressure, hence reducing the base drag. It must be mentioned that this paper covers mainly a variety of passive control methods in the form of the cavity, rib, splitter plate, spike, and some others to regulate the base pressure and drag force. Later, this paper focuses on the control of base pressure in the form of the cavity at a Mach number of 2.2 and an area ratio of 4.84. In this experiment, Computational Fluid Dynamics (CFD) is used to model a convergent-divergent nozzle and a duct. The cavity’s dimensions and locations are studied to get the optimum cavity’s control of base pressure. Two sizes of the cavity are considered which are 3:3 and 6:3. The L/D is varied from 1, 2, 4, and 6 while the Nozzle Pressure Ratio (NPR) ranges from 3 to 16. The 2-D design of a convergent-divergent axisymmetric nozzle suddenly expanded into a duct with a diameter of 22 mm with and without annular rectangular cavities is sketched using ANSYS. The results show that the base pressure is greatly influenced by the cavity’s dimension and location as well as the NPR.