Experimental study of heat transfer to hypersonic nozzle walls

The heat transfer rate from a high enthalpy gas to the walls of a diverging nozzle, through which the gas was flowing, has been experimentally determined. The experimental results are compared with the predictions of several theories for the heat transfer through a laminar boundary layer from a high velocity gas flow. Theories for both reacting and non-reacting gases have been considered. An empirical equation which accounts for the conical flow effects is presented. Experimentally determined rates were found to be as much as ten times as large as predicted values. Discussion of the possible causes of disagreement is included. This discussion indicates the necessity for further investigation using surface temperature thermometers with rapid response, particularly near the nozzle throat. The need for reliable free stream property measurements is also indicated.

Name thesis:degree_name

Master of Science

Level thesis:degree_level

Masters

Discipline thesis:degree_discipline

Engineering

Grantor

Rice University

Year dc:date.issued

1963

Author dc:creator

• Smithson, Jerry Carl

Advisor dc:contributor.advisor

• Wierum, Frederick A.

Statement dc:rights

• Copyright is held by the author, unless otherwise indicated. Permission to reuse, publish, or reproduce the work beyond the bounds of fair use or other exemptions to copyright law must be obtained from the copyright holder.

Language dc:language.iso

eng

Handle dc:identifier.uri

https://hdl.handle.net/1911/89011

OAI identifier oai:identifier

oai:repository.rice.edu:1911/89011