UAV Research – CFD Studies in Venturi Wing Design
Faculty Mentor Name
Shigeo Hayashibara
Format Preference
Poster
Abstract
The purpose of this research is to study the effects of the Venturi Wing Design, which is intended to increase the lift/drag coefficient ratio of UAVs. This new design concept uses Venturi’s effect to create pressure modifications over a wing. The Venturi effect is a concept describing how a reduction in fluid pressure and increase in velocity occurs when fluid flows through a constricted pipe section. To apply this concept, the modified wing was designed with several longitudinal pipes running from the leading edge, the stagnation area where the air normally stops, to the trailing edge of the wing. Since the longitudinal pipes are connected to the stagnation area and the velocity inside of the pipes is higher than the wing upper surface, the air flowing into the pipes will be lower pressure. Additionally, there are two sections of pipes on top of the wing that run down to the longitudinal pipes. These vertical pipes are designed to create a suction that prevents flow separation over the wing. Also, the vertical pipes cause air flow into the canal since the pressure inside of canal is lower than the surface of the wing. Recent CFD simulation with horizontal pipes in a NACA 0012 showed the potential of this design in low Reynolds number condition. This wing design will be used for Society of Automotive Engineers (SAE) Aero West® competition to meet the unique airplane design requirement.
Poster Presentation
EAGLE PRIZE AWARD
Location
AC1-Atrium, Eagle Gym
Start Date
3-23-2018 11:00 AM
End Date
3-23-2018 9:00 PM
UAV Research – CFD Studies in Venturi Wing Design
AC1-Atrium, Eagle Gym
The purpose of this research is to study the effects of the Venturi Wing Design, which is intended to increase the lift/drag coefficient ratio of UAVs. This new design concept uses Venturi’s effect to create pressure modifications over a wing. The Venturi effect is a concept describing how a reduction in fluid pressure and increase in velocity occurs when fluid flows through a constricted pipe section. To apply this concept, the modified wing was designed with several longitudinal pipes running from the leading edge, the stagnation area where the air normally stops, to the trailing edge of the wing. Since the longitudinal pipes are connected to the stagnation area and the velocity inside of the pipes is higher than the wing upper surface, the air flowing into the pipes will be lower pressure. Additionally, there are two sections of pipes on top of the wing that run down to the longitudinal pipes. These vertical pipes are designed to create a suction that prevents flow separation over the wing. Also, the vertical pipes cause air flow into the canal since the pressure inside of canal is lower than the surface of the wing. Recent CFD simulation with horizontal pipes in a NACA 0012 showed the potential of this design in low Reynolds number condition. This wing design will be used for Society of Automotive Engineers (SAE) Aero West® competition to meet the unique airplane design requirement.
Poster Presentation
EAGLE PRIZE AWARD