Integrated supersonic wind tunnel nozzle

Shen, Junmou; Dong, Jingang; Li, Ruiqu; Zhang, Jiang; Chen, Xing; Qin, Yongming; Ma, Handong

doi:10.1016/j.cja.2019.07.005

Cited by 10 publications

(5 citation statements)

References 10 publications

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“…The measurements that are presented in Figure 7 showed that, for all the tested ranges of fan power, the velocity profiles are characterised by a flat profile. The obtained flat velocity profile is a consequence of the use of a specially shaped inlet contraction section designed according to the Witoszynski curve equation [41]. The analysis points out that the differences between the average values determined do not exceed 7.4% of the local value of velocity.…”

Section: Velocity Profiles At the Inlet And Outlet Of The Measurement Sectionmentioning

confidence: 79%

The Use of Capsuled Paraffin Wax in Low-Temperature Thermal Energy Storage Applications: An Experimental and Numerical Investigation

et al. 2021

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The article deals with the experimental and numerical thermal-flow behaviours of a low-temperature Phase Change Material (PCM) used in Thermal Energy Storage (TES) industrial applications. The investigated PCM is a composition that consists of a mixture of paraffin wax capsuled in a melamine-formaldehyde membrane and water, for which a phase change process occurs within the temperature range of 4 °C to 6 °C and the maximum heat storage capacity is equal to 72 kJ/kg. To test the TES capabilities of the PCM for operating conditions close to real ones, a series of experimental tests were performed on cylindrical modules with fixed heights of 250 mm and different outer diameters of 15, 22, and 28 mm, respectively. The module was tested in a specially designed wind tunnel where the Reynolds numbers of between 15,250 to 52,750 were achieved. In addition, a mathematical model of the analysed processes, based on the enthalpy porosity method, was proposed and validated. The temperature changes during the phase transitions that were obtained from the numerical analyses in comparison with the experimental results have not exceeded 20% of the relative error for the phase change region and no more than 10% for the rest. Additionally, the PCM was examined while using a Scanning Electron Microscope (SEM), which indicated no changes in the internal structure during phase transitions and a homogeneous structure, regardless of the tested temperature ranges.

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Section: Velocity Profiles At the Inlet And Outlet Of The Measurement Sectionmentioning

confidence: 79%

The Use of Capsuled Paraffin Wax in Low-Temperature Thermal Energy Storage Applications: An Experimental and Numerical Investigation

et al. 2021

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“…There are several studies including Refs. [17][18][19][20][21][22][23][24][25] which discussed the design of the supersonic wind tunnel with MOC as the common design approach. Additionally, studies such as Refs.…”

Section: Review Of the Theoretical Fundamentalsmentioning

confidence: 99%

A simplified design approach for high-speed wind tunnels. Part I: Table of inclination

et al. 2020

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This study aims to develop a simplified approach for the design of high-speed wind tunnels, operating within the range of Mach 1-4. The study is conducted in two stages; design stage-I consists of the basic parts of a high-speed wind tunnel, i.e. test section and nozzle throat sizes along with the calculations of the minimum pressure ratios necessary for the starting and running of the wind tunnel. Design stage-II is the aerodynamic design of the inlet nozzle contour with the focus on the divergent nozzle section only. In this stage, the fundamental method of characteristics (MOC) is employed by using region-to-region solution approach. Due to the long and complicated procedure of classical MOC, a simpler approach of "table of inclination" is proposed. This inclination table approach is simple in use, highly precise, and efficient which reduces more than 75 % of the calculation time of the MOC. Validation of the nozzle contour design is performed with the Area-Mach ratio relation followed by the results verification obtained from the MATLAB programming. The contour design results of the study are highly accurate (less than 1 % error) which manifests the future possible significance of the inclination table approach for supersonic wind tunnel designs.

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“…A supersonic wind tunnel intended to sustain a flow with a Mach number of 3 in a 30cm by 30cm test section was mentioned by H. Bagheri-Esfe [3]. Shen J et al [4] analysed the integrated supersonic nozzle with Mach numbers 1.5 and 2 to reduce the disturbance arising from the method of characteristics for determining the shape of the supersonic nozzle.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of mini supersonic wind tunnel for flow visualization

Patwa,

Gandhi,

Maharajan

et al. 2023

J. Phys.: Conf. Ser.

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The present study proposes to design, fabricate and investigate a miniature supersonic wind tunnel at an affordable cost, safe to operate, and reliable for education purposes. The configuration consists of a high pressure reservoir, and mini tunnel which will be used for providing the supersonic flow over aerodynamic models. To design the mini supersonic wind tunnel, the method of characteristics is used to ensure that any shocks that arise in contact with the surface do not impact the uniformity and velocity of the flow through the duct. To achieve the supersonic flow, the nozzle contour of the supersonic portion of the wind tunnel is built in such a way that the shocks nullify each other and have zero effect on the velocity of the flow. For compressible flow visualization, an affordable Schlieren setup consisting of a torch, mirrors, and a mobile camera is used for flow visualization. Finally, the visualization results of the present study is in good relation with the theoretical calculations. The present facility is also calibrated by measuring the oblique shock angle in the test section, in the range of Mach number 1.6 to 1.8.

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Integrated supersonic wind tunnel nozzle

Cited by 10 publications

References 10 publications

The Use of Capsuled Paraffin Wax in Low-Temperature Thermal Energy Storage Applications: An Experimental and Numerical Investigation

The Use of Capsuled Paraffin Wax in Low-Temperature Thermal Energy Storage Applications: An Experimental and Numerical Investigation

A simplified design approach for high-speed wind tunnels. Part I: Table of inclination

Experimental investigation of mini supersonic wind tunnel for flow visualization

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