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dc.contributorShih, Yusien_US
dc.date.accessioned2011-03-03T21:51:00Z
dc.date.accessioned2011-08-24T21:44:14Z
dc.date.available2011-03-03T21:51:00Z
dc.date.available2011-08-24T21:44:14Z
dc.date.issued2011-03-03
dc.date.submittedJanuary 2010en_US
dc.identifier.urihttp://hdl.handle.net/10106/5386
dc.description.abstractShock wave/boundary layer interactions (SBLIs) are always an important issue for high-speed vehicles. SBLIs reduce the performance of aerodynamic surfaces and engine inlets, amongst a number of adverse e ects. Micro-vortex generators (MVGs) are a potential ow control method that has seen intense investigation recently and have even been implemented in actual con gurations at low speeds. The present research is focused on the mean pressures at Mach 2.5 around an MVG. Experiments were performed with a baseline at plate and also with two MVG con gurations (70 and 45 trailing edge) mounted ahead of a 5 ramp. In the present study MVGs are used to manipulated the ow within the boundary layer and the e ects on the weak oblique shock produced by the 5 ramp are recorded. The results appeared similar to the large eddy simulations reported by Li and Liu [1] and [2]. Three conclusions can be made in present research 1. The di erent behaviors of SBLI, with MVG and without MVG, were observed from mean pressure measurements. 2. The mean pressure right behind MVG is lower, compared to the mean pressure in the middle of two MVGs. 3. The trailing angle of the MVG does a ect the mean pressure distribution.en_US
dc.language.isoenen_US
dc.publisherAerospace Engineeringen_US
dc.titleMean Pressure Measurements Of Micro-vortex Generator At Mach 2.5en_US
dc.typeM.S.en_US


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