An experimental investigation of the flow field near liquid fuel jets injected transverse to a hot supersonic air stream

The flow field associated with injecting liquid fuel jets into a hot, supersonic air stream was investigated for three different liquids; kerosene, carbon disulfide and water as a non-burning control. The tests were conducted at a Mach number of 1.8 with a nominal stagnation pressure of 100 psia and the stagnation temperature was varied from 500°F to 2100°F. The flow field was observed by means of direct, top-view photographs, infrared, top-view photographs and nozzle wall temperature measurements, one under the liquid surface formed and the other well removed from it. The infrared photographs are produced by a Thermographic camera which senses the radiation emitted by the surfaces and internally processes these signals to produce a color isotherm image on a color television screen. The nozzle wall temperature was varied from 250°F to 900°F. For each method of observation, there seemed to be indications that combustion was occurring on the liquid surface layer. However, none of these cases overlapped from one method to another, and as a result, it was difficult to ascertain that combustion did occur. Further testing is needed.

Name thesis:degree_name

Master of Science

Level thesis:degree_level

masters

Discipline thesis:degree_discipline

Aerospace Engineering

Department dc:contributor.department

Aerospace Engineering

Grantor dc:publisher

Virginia Polytechnic Institute and State University

Year dc:date.issued

1976

Author dc:creator

• McVey, William James

Statement dc:rights

• In Copyright

Licence dc:rights.uri

• http://rightsstatements.org/vocab/InC/1.0/

Language dc:language.iso

en

Handle dc:identifier.uri

http://hdl.handle.net/10919/71087

OAI identifier oai:identifier

oai:vtechworks.lib.vt.edu:10919/71087