Zobrazeno 1 - 6
of 6
pro vyhledávání: '"Hypersonic Shock Tunnel (HST2)"'
Autor:
Philip, Sarah Jobin
Aerodynamic cavities are common features on hypersonic vehicles which are caused in both large and small scale features like surface defects, pitting, gap in joints etc. In the hypersonic regime, the presence of such cavities alters the flow phenomen
Externí odkaz:
http://etd.iisc.ernet.in/2005/3900
http://etd.iisc.ernet.in/abstracts/4775/G25303-Abs.pdf
http://etd.iisc.ernet.in/abstracts/4775/G25303-Abs.pdf
Autor:
Thakur, Ruchi
One of the characteristics of the high speed ows over blunt bodies is the detached shock formed in front of the body. The distance of the shock from the stagnation point measured along the stagnation streamline is termed as the shock stand o distance
Externí odkaz:
http://etd.iisc.ernet.in/2005/3848
http://etd.iisc.ernet.in/abstracts/4720/G27111-Abs.pdf
http://etd.iisc.ernet.in/abstracts/4720/G27111-Abs.pdf
Autor:
Nagashetty, K
In the flying field of space transportation domain, the increased efforts involving design and development of hypersonic flight for space missions is on toe to provide the optimum aerothermodynamic design data to satisfy mission requirements. Aerothe
Externí odkaz:
http://hdl.handle.net/2005/3195
http://etd.ncsi.iisc.ernet.in/abstracts/4067/G26579-Abs.pdf
http://etd.ncsi.iisc.ernet.in/abstracts/4067/G26579-Abs.pdf
Autor:
Srinath, S
The 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 forwa
Externí odkaz:
http://hdl.handle.net/2005/1116
Autor:
Joarder, Ratan
For flights beyond Mach 6 ramjets are inefficient engines due to huge total pressure loss in the normal shock systems, combustion conditions that lose a large fraction of the available chemical energy due to dissociation and high structural loads. Ho
Externí odkaz:
http://hdl.handle.net/2005/1005
Autor:
Reddeppa, P
Knowledge of flow separation is very essential for proper understanding of both external and internal aerothermodynamics of bodies. Because of unique flow features such as thick boundary layers, merged shock layers, strong entropy layers, flow separa
Externí odkaz:
http://hdl.handle.net/2005/586