Date of Award:

5-2026

Document Type:

Thesis

Degree Name:

Master of Science (MS)

Department:

Mechanical and Aerospace Engineering

Committee Chair(s)

Douglas F. Hunsaker

Committee

Douglas F. Hunsaker

Committee

Jennifer van Rij

Committee

Stephen A. Whitmore

Abstract

Numerical lifting-line is a tool that can be used to evaluate the forces and moments of an aircraft wing. This method has limitations but it is beneficial in obtaining a large set of results with relatively little computational power. This research seeks to analyze two different flight scenarios through the use of two numerical lifting-line tools developed at the Utah State University AeroLab. The first scenario involves an aircraft in ground effect flight. When an aircraft flies close to the ground, a phenomenon called ground effect occurs where the lift is increased and the induced drag is decreased. Therefore, flying in ground effect can significantly improve the overall efficiency of an aircraft. This research specifically analyzes the wing geometry to determine the wing angle which produces the least amount of induced drag in ground effect flight. The second case study compares two aircraft in an aerial refueling configuration. Aerial refueling is a common method used to extend the flight time of an aircraft where a large tanker distributes fuel into another aircraft midflight. The tanker has a significant impact on the airflow surrounding it which can make it difficult for other aircraft in the vicinity to maneuver. The interaction of a vertical tail with the surrounding airflow can contribute to an increase in side force, potentially making it more difficult for an aircraft to maintain position behind a tanker. Rather than using a traditional vertical tail, the Bio-Inspired Rotating Empennage (BIRE) aircraft uses a design similar to that of a bird in which the entire tail can rotate to provide necessary stability. This research seeks to analyze the forces and moments experienced by the BIRE aircraft in aerial refueling. Results are compared to that of a standard aircraft with a conventional vertical tail.

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