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ColinWTrussa_MastersThesis_2020.pdf (5.12 MB)

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Low-Speed Aerodynamic Characteristics of a Delta Wing with Deflected Wing Tips

Trussa, Colin Weidner
http://orcid.org/0000-0002-3768-0754
http://rave.ohiolink.edu/etdc/view?acc_num=osu1586450691890636

Abstract Details

2020, Master of Science, Ohio State University, Aero/Astro Engineering.
The purpose of this work was to investigate the low-speed aerodynamic characteristics of a novel delta wing layout with deflected wing tips. This project is motivated by the ongoing unmanned aerial vehicle research and development at The Ohio State University Aerospace Research Center. The model under test for this study had four main design requirements: (1) high-speed, (2) highly maneuverable, (3) aerodynamically interesting, and (4) multi-configurable. The last three requirements are addressed directly in this report with specific emphasis on requirements two and three. A modular fuselage design satisfied requirement four, and the novel delta wing addressed requirements two and three. The novel delta wing has a leading-edge sweep of 60 degrees, a high-speed airfoil with a rounded leading-edge, and wing tips that can rotate a full 180 degrees about a hinge, located at 2/3rds of the half-span parallel to fuselage centerline. Three different wing tip deflection configurations were analyzed: positive, negative, and asymmetric. Positive wing tip deflection corresponds to the wing tips being deflected up towards the vertical tail. Negative wing tip deflection is when the wing tips are deflected down, away from the vertical tail. While the asymmetric configuration has one wing tip deflected up and the other down. Analysis on the model was completed using a panel method code and experimental wind tunnel testing. The panel method code used was OpenVSP. Upon implementing a vortex lift factor, it was determined that the delta wing results from OpenVSP were only useful for lift related data after comparing the panel method results to theory and publicly available delta wing data. The wind tunnel used for this work is located at the Aerospace Research Center. The wind tunnel is an open circuit subsonic wind tunnel with a 3’x5’ test section. Aerodynamic forces were measured using an internal six-component force balance. Tests were performed at two different Reynolds numbers, 3.65x105 and 5x105. Significant results from wind tunnel testing found that as the wing tip deflection is increased, for all three layouts, the static longitudinal stability of the model decreased with no significant loss in lift characteristics. The adjustable stability as a result of rotating a delta wing’s wing tips, provides inflight adjustments to the maneuverability characteristics of the aircraft.
Clifford Whitfield, Dr. (Advisor)
Rick Freuler, Dr. (Committee Member)
Matthew McCrink, Dr. (Committee Member)
100 p.
Aerospace Engineering
delta wing; deflected wing tips; low-speed aerodynamics

Recommended Citations

Citations

  • Trussa, C. W. (2020). Low-Speed Aerodynamic Characteristics of a Delta Wing with Deflected Wing Tips [Master's thesis, Ohio State University]. OhioLINK Electronic Theses and Dissertations Center. http://rave.ohiolink.edu/etdc/view?acc_num=osu1586450691890636

    APA Style (7th edition)

  • Trussa, Colin. Low-Speed Aerodynamic Characteristics of a Delta Wing with Deflected Wing Tips. 2020. Ohio State University, Master's thesis. OhioLINK Electronic Theses and Dissertations Center, http://rave.ohiolink.edu/etdc/view?acc_num=osu1586450691890636.

    MLA Style (8th edition)

  • Trussa, Colin. "Low-Speed Aerodynamic Characteristics of a Delta Wing with Deflected Wing Tips." Master's thesis, Ohio State University, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1586450691890636

    Chicago Manual of Style (17th edition)

osu1586450691890636
10,368
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