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An investigation of canted adjustable endplates for the control of drag
Clements, Harry R.
Clements, Harry R.
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1954-04
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Electronic dissertations
Electronic dissertations
Electronic dissertations
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Abstract
Wind tunnel tests were conducted on a model wing with a Clark Y
airfoil section. The wing, which had an aspect ratio of 5 with no taper,
was made with a full span leading edge slot and a 30% chord slotted flap.
Wing tip end plates with a height of 20% of the wing span were attached
to the model. The end plates had an NACA 0012 airfoil section, had no taper,
and were constructed with a 30% chord plain flap.
The angle that the end-plate made with the approaching stream flow was
adjustable. The end-plate at each wing tip was constructed in two sections,
one to fit above the wing and one to fit below the wing. In this manner the
end-plates sections could be made to have opposite deflections.
The wing end-plate combination was tested for various deflections of the
end-plate or end-plate flap. For all tests the wing flap deflection was $50^\circ$,
and wing angle of attack was varied. Force measurements were taken to determine
lift, drag, and pitching moment coefficients. Only the most promising configurations
are discussed here, and for these, flow visualization tests were
made by photographing a tuft grid placed behind the model.
Some results obtained from the force tests are shown in Table I. For
these configurations, end-plate and end-plate flap deflections are designated
according to their intended result on drag, that is + for increase drag and
- for decrease. The + designation indicates that the trailing edge of the endplate
or flap on the upper wing surface was deflected inboard, and the trailing
edge of the end-plate or flap on the lower wing surface was deflected outboard.
For the - designation all trailing edge positions were opposite to those specified
for the + designation.
Table of Contents
List of figures and phoographs -- List of symbols -- Introduction -- Theory -- Wind tunnel investigation -- Application -- Conclusions -- References -- Graphs and photographs
Description
Thesis (M.S.)-- University of Wichita, College of Engineering, Dept. of Aeronautical Engineering
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Wichita State University
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Wichita State University