Data reduction for the unsteady aerodynamics on a circulation control airfoil.
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Authors
Pickelsimer, Billy Murel
Subjects
Advisors
Schmidt, Louis V.
Date of Issue
1977-03
Date
Publisher
Monterey, CA; Naval Postgraduate School
Language
en_US
Abstract
Calculating the lift, drag, and pitching moment coefficients for an airfoil from the static pressure distribution obtained from wind tunnel tests is routine task when steady flow is considered, but it, is much more complicated when the airfoil is operating in an unsteady flow field, similar to that experienced by a helicopter rotor blade, produced by an oscillating wind tunnel. A data reduction routine capable of condensing the large numbers of data associated with the unsteady investigation, as well as a numerical integration algorithm for the unsteady aerodynamic coefficients, were developed; however, no unsteady data were collected due to hardware failures. The ability of the program was demonstrated on previously obtained steady and quasi-steady data and sample results were presented.
Type
Thesis
Description
This thesis prepared in conjunction with research
supported by the Naval Air Systems Command 370C.
Series/Report No
Department
Aeronautics