An experimental study of flow over a 6 to 1 prolate spheroid at incidence

In two-dimensional flow, the point of flow separation from the surface coincides with the point at which the skin friction vanishes. However, in three-dimensional flow, the situation is much more complex and the flow separation is rarely associated with the vanishing of the wall shear stress except in a few special cases. Though the effects of cross-plane separation are substantial and have been recognized for some time, the phenomenon of flow separation over three-dimensional bodies is still far from being completely understood. The flow is so complex that no completely satisfactory analytical tools are available at the moment. In an attempt to logically identify the various effects and parametric dependence while simultaneously minimizing configuration dependent issue, the flow over a 6 to 1 prolate spheroid, which is a generic three-dimensional body, is investigated. For the identification of the general flow pattern and better understanding of the flow field, surface-oil-flow visualization tests and force and moment tests were performed. The angle of attack effect and Reynolds number effect on the separation location are studied with natural transition. Forces and moments tests, surface pressure distribution measurements as well as the surface presure fluctuations, and mini-tuft flow visualization tests were made to document the flow characteristics on the surface of the body with an artificial boundary layer trip. It was found that there exists a critical Reynolds number at which the flow characteristics of the afterbody changes. This critical Reynolds number was also confirmed by the force and moment tests. Above this Reynolds number, as the Reynolds number increases, the separation lines do not change their circumferential location but stretch to the upstream of the body. For the low supercritical Reynolds number range, the angle of attack effect on the location of the primary separation is not as prominent as in the higher Reynolds number range where the cross-flow component effect becomes dominant. Surface pressure fluctuation data and surface pressure spectra were measured and documented for the first time for this type of three-dimensional flow. For the extension of the study to unsteady transient motion effects, a new Dynamic-Plunge-Pitch-Roll (DyPPiR) model mount was designed and developed to generate required transient motions. The measurements carried out during this study are to be used as reference data to identify the unsteady transient effect of the flow field undergoing unsteady transient maneuvers.

Name thesis:degree_name

Ph. D.

Level thesis:degree_level

doctoral

Discipline thesis:degree_discipline

Aerospace Engineering

Department dc:contributor.department

Aerospace Engineering

Grantor dc:publisher

Virginia Tech

Year dc:date.issued

1992

Author dc:creator

• Ahn, Seungki

Chair dc:contributor.committeechair

• Simpson, Roger L.

Committee members dc:contributor.committeemember

• Schetz, Joseph A.
• Lutze, Frederick H. Jr.
• Mason, William H.
• Walker, Dana A.

Statement dc:rights

• In Copyright

Licence dc:rights.uri

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

Language dc:language.iso

en

Dc Identifier Other

etd-06062008-165846

OAI identifier oai:identifier

oai:vtechworks.lib.vt.edu:10919/38361