Investigation of subsonic boundary layer effects on supersonic-type airfoil sections

It was found in this investigation that the testing of supersonic airfoils at subsonic speeds to obtain pressure distributions will result in considerable error if the models are tested at very low Reynolds Numbers. The thickness of the boundary layer is critical at low Reynolds Numbers and causes a decrease in the overpressure region. This, coupled with the fact that the overpressure region increases more with Mach Number than predicted by the theory, could lead to erroneous calculations of the drag.

Name thesis:degree_name

Master of Science

Level thesis:degree_level

masters

Discipline thesis:degree_discipline

Applied Mechanics

Department dc:contributor.department

Applied Mechanics

Grantor dc:publisher

Virginia Tech

Year dc:date.issued

1952

Author dc:creator

• West, Charles Dorman

Chair dc:contributor.committeechair

• Maher, Francis J.

Committee members dc:contributor.committeemember

• Truitt, Robert W.
• Norris, Earle Bertram
• Pardue, Louis 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-09082012-040341

OAI identifier oai:identifier

oai:vtechworks.lib.vt.edu:10919/44662