Abstract Title

Aerodynamic Effects of a Two Parallel Forward Swept Flat Plates

Faculty Mentor Name

Jeffrey C. Ashworth

Format Preference

Poster

Abstract

The purpose of this study is to analyze the orientation of two parallel forward swept flat plates or “wing” segments and the aerodynamic effects based on their orientation. This orientation is necessary for a possible wing design that is capable of rotating and retracting into the fuselage of an aircraft. A wing with this capability would be very useful on a Reusable Launch Vehicle (RLV) where the wing could be retracted into the fuselage to greatly reduce the drag while an external rocket engine is ignited to boost the aircraft into Low Earth Orbit (LEO). The model will consist of two plates of equal geometry that are parallel to one another. The aerodynamic effects of two parallel plates will be examined where the downwash from the first plate is swept underneath the second plate. The data collected will include the pitching moments of the wings at a 15° tilt, as well as the lift coefficient and drag coefficient associated with this orientation. The data will reveal whether or not the design is applicable based on the stability of the orientation of the wings during flight. If the current design is not applicable on a RLV, possible other uses include a fighter jet as deployment/ retraction would occur while the aircraft is stationary and would only be used for storage of said aircraft.

Poster Presentation

IGNITE GRANT AWARD

Location

AC1-ATRIUM

Start Date

4-8-2016 1:00 PM

End Date

4-8-2016 3:00 PM

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Apr 8th, 1:00 PM Apr 8th, 3:00 PM

Aerodynamic Effects of a Two Parallel Forward Swept Flat Plates

AC1-ATRIUM

The purpose of this study is to analyze the orientation of two parallel forward swept flat plates or “wing” segments and the aerodynamic effects based on their orientation. This orientation is necessary for a possible wing design that is capable of rotating and retracting into the fuselage of an aircraft. A wing with this capability would be very useful on a Reusable Launch Vehicle (RLV) where the wing could be retracted into the fuselage to greatly reduce the drag while an external rocket engine is ignited to boost the aircraft into Low Earth Orbit (LEO). The model will consist of two plates of equal geometry that are parallel to one another. The aerodynamic effects of two parallel plates will be examined where the downwash from the first plate is swept underneath the second plate. The data collected will include the pitching moments of the wings at a 15° tilt, as well as the lift coefficient and drag coefficient associated with this orientation. The data will reveal whether or not the design is applicable based on the stability of the orientation of the wings during flight. If the current design is not applicable on a RLV, possible other uses include a fighter jet as deployment/ retraction would occur while the aircraft is stationary and would only be used for storage of said aircraft.

Poster Presentation

IGNITE GRANT AWARD