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dc.contributor.advisorJagadeesh, G
dc.contributor.authorSrinath, S
dc.date.accessioned2011-04-06T04:30:40Z
dc.date.accessioned2018-07-31T05:18:27Z
dc.date.available2011-04-06T04:30:40Z
dc.date.available2018-07-31T05:18:27Z
dc.date.issued2011-04-06
dc.date.submitted2009
dc.identifier.urihttp://etd.iisc.ac.in/handle/2005/1116
dc.description.abstractThe emerging and competitive environment in the space technology requires the improvements in the capability of aerodynamic vehicles. This leads to the analysis in drag reduction of the vehicle along with the minimized heat transfer rate. Using forward facing solid aerospike is the simplest way among the existing drag reduction methodologies for hypersonic blunt cone bodies. But the flow oscillations associated with this aerospike makes it difficult to implement. When analyzing this flow, it can be understood that this oscillating flow can be compared to conical cavity flow. Therefore in the spiked flows, it is decided to implement the technique used in reducing the flow oscillation of the cavities. Based on this method the shallow conical cavity flow generated by the aerospike fixed ahead of a 120o blunt cone body is fissured as multiple cavities by so many disks formed from 10o cone. Now the deep conical cavities had the length to mean depth ratio of unity; this suppresses the unnecessary oscillations of the shallow cavity. The total length of the telescopic aerospike is fixed as 100mm. And one another conical tip plain aerospike of same length is designed for comparing the telescopic spike’s performance at hypersonic flow Mach numbers of 5.75 and 7.9. A three component force balance system capable of measuring drag, lift and pitching moment is designed and mounted internally into the skirt of the model. Drag measurement is done for without spike, conical tip plain spiked and telescopic spiked blunt cone body. The three configurations are tested at different angles of attack from 0 to 10 degree with a step of 2. A discrete iterative deconvolution methodology is implemented in this research work for obtaining the clean drag history from the noisy drag accelerometer signal. The drag results showed the drag reduction when compared to the without spike blunt cone body. When comparing to the plain spiked, the telescopic spiked blunt cone body has lesser drag at higher angles of attack. Heat transfer measurements are done over the blunt cone surface using the Platinum thin film gauges formed over the Macor substrate. These results and the flow visualization give better understanding of the flow and the heat flux rate caused by the flow. The enhancement in the heat flux rate over the blunt cone surface is due to the shock interaction. And in recirculation region the heat flux rate is very much lesser when compared to without spike blunt cone body. It is observed that the shock interaction in the windward side is coming closer towards the nose of the blunt cone as the angle of attack increases and the oscillation of the oblique shock also decreases. Schlieren visualization showed that there is dispersion in the oblique shock, particularly in the leeward side. In the telescopic spike there are multiple shocks generated from each and every disk which coalesces together to form a single oblique shock. And the effect of the shock generated by the telescopic spike is stronger than the effect of the shock generated by the conical tip plain spike.en_US
dc.language.isoen_USen_US
dc.relation.ispartofseriesG23608en_US
dc.subjectHypersonic Aerodynamicsen_US
dc.subjectAerospikeen_US
dc.subjectHypersonic Mach Numbersen_US
dc.subjectHypersonic Flowen_US
dc.subjectDrag (Aerodynamics)en_US
dc.subjectAerodynamic Heatingen_US
dc.subjectCone-Aerodynamicsen_US
dc.subjectTelescopic Aerospikeen_US
dc.subjectHypersonic Shock Tunnel HST2en_US
dc.subjectBlunt Coneen_US
dc.subject.classificationAeronauticsen_US
dc.titleExperimental Study Of Large Angle Blunt Cone With Telescopic Aerospike Flying At Hypersonic Mach Numbersen_US
dc.typeThesisen_US
dc.degree.nameMSc Enggen_US
dc.degree.levelMastersen_US
dc.degree.disciplineFaculty of Engineeringen_US


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