Development of a Supersonic Aerodynamic Test Section Using Computational Modeling

Mitchell, Richard R.; Lu, Frank K.

doi:10.2514/6.2009-3573

Cited by 6 publications

(6 citation statements)

References 15 publications

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“…The duration of the flow visualization experiments was less than 10 s long which resulted in a total temperature drop of only 1-2 K. Thus, despite the blowdown nature of the tunnel, the temperature can be considered to be steady for the present experiments. With the relatively steady total pressure and temperature, the unit Reynolds number can also be considered to be steady at 43 million per m. 25 over which a boundary layer was developed naturally as shown schematically in Fig. 4.…”

Section: A Facility and Test Hardwarementioning

confidence: 99%

Experimental and Numerical Study of Flow Topology Past Micro-Vortex Generators

Pierce

Shih

et al. 2010

40th Fluid Dynamics Conference and Exhibit

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Detailed experimental and numerical visualizations of the flow past a micro vortex generator (MVG) in the form of a ramp with swept sides in a Mach 2.5 flow revealed a complex near-field topology. The incoming flow separated over the leading edge of the MVG despite the ramp angle being below the threshold for incipient separation. The separation over the MVG protuberance produced a weak trailing horseshoe vortex system. The attachment line shows a saddle/foci combination on each side of a nodal point of attachment. The flow over the top of the MVG separated off the slant edges to produce a large primary vortex pair. This large primary vortex pair induced two secondary vortex filament pairs, one off the top of the MVG and another at the corner of the MVG with the flat plate. Extra complexities were revealed at the trailing edge with at least two pairs of saddle/foci combinations observed. It is postulated that vortex filaments spring from the various saddle/foci combinations as these were not observed experimentally or computationally. Symmetry breaking due to flow unsteadiness was also observed in the MVG wake.

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Section: A Facility and Test Hardwarementioning

confidence: 99%

Experimental and Numerical Study of Flow Topology Past Micro-Vortex Generators

Pierce

Shih

et al. 2010

40th Fluid Dynamics Conference and Exhibit

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“…Very thick boundary layer exists between the supersonic flow and the walls of the contraction section of the diffuser. 21,22 In ejector, the flow starts from the cluster nozzle exit that remains supersonic up to downstream of the ejector throat.…”

Section: Case 1 (Without Model)mentioning

confidence: 99%

A numerical optimization of high altitude testing facility for wind tunnel experiments

Rose

Jinu²,

Brindha

2015

Chinese Journal of Aeronautics

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High altitude test facilities are required to test the high area ratio nozzles operating at the upper stages of rocket in the nozzle full flow conditions. It is typically achieved by creating the ambient pressure equal or less than the nozzle exit pressure. On average, air/GN 2 is used as active gas for ejector system that is stored in the high pressure cylinders. The wind tunnel facilities are used for conducting aerodynamic simulation experiments at/under various flow velocities and operating conditions. However, constructing both of these facilities require more laboratory space and expensive instruments. Because of this demerit, a novel scheme is implemented for conducting wind tunnel experiments by using the existing infrastructure available in the high altitude testing (HAT) facility. This article presents the details about the methods implemented for suitably modifying the sub-scale HAT facility to conduct wind tunnel experiments. Hence, the design of nozzle for required area ratio A/A * , realization of test section and the optimized configuration are focused in the present analysis. Specific insights into various rocket models including high thrust cryogenic engines and their holding mechanisms to conduct wind tunnel experiments in the HAT facility are analyzed. A detailed CFD analysis is done to propose this conversion without affecting the existing functional requirements of the HAT facility.

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“…Thus, the unit Reynolds number can also be considered to be steady at 43 both sides and from the top. A flat plate, 73 cm long (28.75 in), with a sharp leading edge of 15 deg was mounted in the test section 44 over which a boundary layer was developed naturally (Fig. 3).…”

Section: A Background On Micro Vortex Generators For High-speed Applmentioning

confidence: 99%

New Seeding and Surface Treatment Methods for Particle Image Velocimetry

Pierce

2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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PIV systems rely on a combination of seed particles, laser light intensity, and camera positioning to collected velocity data. Careful attention is needed when selecting the appropriate setup configuration for PIV systems. This paper focuses on several areas for improvement in PIV data collection for a compressible turbulent boundary layer study on a flat plate using MVG's. The topics include determining the seed particle surface preparation for a flat plate, and PIV system configuration. Nomenclature α divergence angle d laser beam diameter f focal length d p particle diameter ρ p particle density µ dynamic viscosity τ particle relaxation time

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Development of a Supersonic Aerodynamic Test Section Using Computational Modeling

Cited by 6 publications

References 15 publications

Experimental and Numerical Study of Flow Topology Past Micro-Vortex Generators

Experimental and Numerical Study of Flow Topology Past Micro-Vortex Generators

A numerical optimization of high altitude testing facility for wind tunnel experiments

New Seeding and Surface Treatment Methods for Particle Image Velocimetry

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