The Effect of Reynolds Number on the Flow Field About a 70° Cone

Author: Bevernick, Richard Alexander

Year: 1949

Degree: Engineer's thesis

Advisor: Puckett, Allen E.

Committee Member: Unknown, Unknown

Option: Aeronautics

DOI: 10.7907/FGSF-5183

Abstract

This investigation has undertaken to measure the possible Reynolds number effects in the flow field about a 70° finite cone in a supersonic flow. The principal means of observing such effects was by static pressure measurements at the surface of the cone.

Results indicate that such effects do exist when the free stream Mach number is low enough to produce subsonic flow over the face of the cone, but they are slight. At very low Reynolds numbers with a detached shock, some decrease in static pressure on the surface of the cone results, apparently due to increased boundary layer. Over the entire range of Reynolds numbers investigated with either attached or detached shock, an increase in static pressure on the cone face at some distance from the apex results from increased Reynolds number, apparently due to the shoulder disturbance.

The investigation was conducted at GALCIT as the basis for a thesis in partial fulfillment for the professional degree of Aeronautical Engineer.

Files