Aerodynamic Analysis of a U.S. Navy and Marine Corps Unmanned Air Vehicle

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Aerodynamic Analysis of a U.S. Navy and Marine Corps Unmanned Air Vehicle

D. F. Lyons

An aerodynamic analysis was performed on a U.S. Navy and Marine Corps Unmanned Air Vehicle (UAV) called PIONEER. A low-order panel method called PMARC (Panel Method Ames Research Center) was used to obtain various aerodynamic parameters and to evaluate the longitudinal and directional stability and control of the vehicle. In addition, a drag analysis of the vehicle was performed using techniques described in Fluid Dynamic Drag by Hoerner. Drag reduction methods were also investigated. The neutral point of the large tail PIONEER was calculated to be at 74% of the mean aerodynamic chord (MAC). The small tail neutral point was calculated to be at the 51%MAC position. Cross wind limitations were obtained for PIONEER. The maximum sideslip angles due to cross wind were determined to be 8.5 and 18. For an approach speed of 65 knots, cross wind limits were calculated to be ten knots and 22 knots for the single rubber and dual rudder cases, respectively. Drag polars were plotted for PIONEER. It was determined that drag on the vehicle could be reduced by 29% using simple and cost effective modifications to the vehicle. Follow-on analysis of PIONEER through the Naval Postgraduate School UAV Flight Test Research Program and through full-scale wind tunnel testing at the National Full-Scale Aerodynamics Complex were also discussed. Keywords: Remotely piloted vehicles, Military aircraft, Flight testing, Stability and control. (sdw)