Type of Document Master's Thesis Author Plumley, Ryan W. Author's Email Address email@example.com URN etd-03052008-083551 Title Conceptual Assessment of an Oblique Flying Wing Aircraft Including Control and Trim Characteristics Degree Master of Science Department Aerospace and Ocean Engineering Advisory Committee
Advisor Name Title Mason, William H. Committee Chair Patil, Mayuresh J. Committee Member Woolsey, Craig A. Committee Member Keywords
- Stability and Control
- Vortex Lattice
- Oblique Flying Wing
- Wave Drag
Date of Defense 2008-02-22 Availability unrestricted AbstractA method was developed to assist with the understanding of a unique configuration and investigate some of its stability and control attributes. Oblique wing aircraft concepts are a design option that is well understood, but has yet to be used in a production aircraft. Risk involved in choosing such a design can be averted through additional knowledge early in the concept evaluation phase.
Analysis tools commonly used in early conceptual level analysis were evaluated for applicability to a non-standard aircraft design such as an oblique flying wing. Many tools used in early analyses make assumptions that are incompatible with the slewed wing configuration of the vehicle.
Using a simplified set of tools, an investigation of a unique configuration was done as well as showing that the aircraft could be trimmed at given conditions. Wave drag was investigated to determine benefits for an oblique flying wing. This form of drag was reduced by the distribution of volume afforded by the slewing of the aircraft’s wing. Once a reasonable concept was developed, aerodynamic conditions were investigated for static stability of the aircraft. Longitudinal and lateral trim were established simultaneously due to its asymmetric nature.
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