The Effects of Upper Surface Modifications on Low Reynolds's Flight
Faculty Mentor Name
Lance Traub
Format Preference
Oral Presentation
Abstract
The research conducted was focused on manipulating the upper surface boundary layer over an airfoil through controlling transition. This control would prove beneficial for low Reynold’s flight by reducing the pressure drag on airfoil, which could significantly improve the efficiency of small unmanned aerial vehicles. The models used in testing contained two different types of upper surface modifications. The first set was based around a series of circular extrusions, the circles were varied by size, depth, and spacing. The second set of models were based on a triangular ramp similar to that of a NACA inlet, the ramps were varied by size, depth, and spacing. The results of testing thus far has shown that the model with the deepest circular extrusion experiences a shift in its zero angle of attack while the model with the greatest distance between circles illustrated an early reattachment of the separated flow. Testing of the NACA inlets is still under way, although some preliminary results show that certain models have their lowest drag at a point where positive lift is being generated.
Ignite Grant Award
Location
AC1-118
Start Date
4-10-2015 12:00 PM
End Date
4-10-2015 12:15 PM
The Effects of Upper Surface Modifications on Low Reynolds's Flight
AC1-118
The research conducted was focused on manipulating the upper surface boundary layer over an airfoil through controlling transition. This control would prove beneficial for low Reynold’s flight by reducing the pressure drag on airfoil, which could significantly improve the efficiency of small unmanned aerial vehicles. The models used in testing contained two different types of upper surface modifications. The first set was based around a series of circular extrusions, the circles were varied by size, depth, and spacing. The second set of models were based on a triangular ramp similar to that of a NACA inlet, the ramps were varied by size, depth, and spacing. The results of testing thus far has shown that the model with the deepest circular extrusion experiences a shift in its zero angle of attack while the model with the greatest distance between circles illustrated an early reattachment of the separated flow. Testing of the NACA inlets is still under way, although some preliminary results show that certain models have their lowest drag at a point where positive lift is being generated.
Ignite Grant Award