Design of a Flow Diverting Device for OH-58A+ Helicopters

A preliminary design of a flow diverter and flow visualization system was accomplished based on earlier water tunnel test results concluded in December 1997 at the University of Tennessee Space Institute. The purpose of this effort was to conduct a rapid prototype of the concept system and flight test the equipment on an OH-58A+ helicopter. The rapid prototyping included design, fabrication, and installation of an airworthy airflow-diverting device for full-scale helicopter flight evaluations (Figure 1). This device was tested on an OH-58A+ helicopter for handling qualities, level flight performance, fuselage airflow changes, and operational utility.