An investigation of canted adjustable endplates for the control of drag
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
Thesis (M.S.)-- University of Wichita, College of Engineering, Dept. of Aeronautical Engineering