Record Details

Experimental Investigations on Hypersonic Waverider

Electronic Theses of Indian Institute of Science

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Field Value
 
Title Experimental Investigations on Hypersonic Waverider
 
Creator Nagashetty, K
 
Subject Hypersonic Waverider
Aerothermodynamics
Hypersonic Aerodynamics
Aerodynamics
Hypersonic Shock Tunnel - Heat Transfer
Hypersonic Shock Tunnel HST2
Flow Visualization
Shock Wave Loading
Hypersonic Mach Numbers
Aerospace Engineering
 
Description 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. Aerothermodynamics is the basis for designing and development of hypersonic space transportation flight vehicles such as X 51 a, and other programmes like planetary probes for Moon and Mars, and Earth re-entry vehicles such as SRE and space shuttle. It enables safe flying of aerospace vehicles, keeping other parameters optimum for structural and materials with thermal protection systems. In this context, the experimental investigations on hypersonic waverider are carried out at design Mach 6.
The hypersonic waverider has high lift to drag ratio at design Mach number even at zero degree angle of incidence, and this seems to be one of the special characteristics for its shape at hypersonic flight regime. The heat transfer rates are measured using 30 thin film platinum gauges sputtered on a Macor material that are embedded on the test model. The waverider has 16 sensors on top surface and 14 on bottom surface of a model. The surface temperature history is directly converted to heat transfer rates. The heat transfer data are measured for design (Mach 6) and off-design Mach numbers (8) in the hypersonic shock tunnel, HST2. The results are obtained at stagnation enthalpy of ~ 2 MJ/kg, and Reynolds number range from 0.578 x 106 m-1 to 1.461 x 106 m-1. In addition, flow visualization is carried out by using Schlieren technique to obtain the shock structures and flow evolution around the Waverider. Some preliminary computational analyses are conducted using FLUENT 6.3 and HiFUN, which gave quantitative results. Experimentally measured surface heat flux data are compared with the computed one and both the data agree well. These detailed results are presented in the thesis.
 
Contributor Reddy, K P J
 
Date 2018-02-27T19:22:17Z
2018-02-27T19:22:17Z
2018-02-28
2014
 
Type Thesis
 
Identifier http://hdl.handle.net/2005/3195
http://etd.ncsi.iisc.ernet.in/abstracts/4067/G26579-Abs.pdf
 
Language en_US
 
Relation G26579