Date of Defense

Spring 4-11-1995

First Advisor

Parviz Merati, Mechanical and Aeronautical Engineering


A wing was designed for a remotely piloted vehicle to be flown in an inter-collegiate competition. Design requirements were to maximize the lift and minimize the drag. Two critical aspects of a high-lift wing were considered: the airfoil shape and wing configuration. After researching modern airfoils, a number were selected for further analysis. These airfoils were analyzed with computer simulation codes, and slight modifications were made to increase performance characteristics. The best airfoils were then modeled and tested in a water tunnel using a five-component electronic balance system to obtain precise experimental data. With the research and testing completed, the wing configuration was designed. Structure and materials were chosen such that the wing was structurally sound. Final dimensioning, including aspect ratio and wingtip shape, was left to the RPV stability and control design team.

Access Setting

Honors Thesis-Campus Only