Dissertation/Thesis Abstract

Wind tunnel test of a tailless aircraft with a belly-flap control surface used in combination with wing flaps
by Dougherty, Daniel A., M.S., California State University, Long Beach, 2012, 79; 1517618
Abstract (Summary)

A wind tunnel tat of a tailless aircraft configuration that has been quipped with a belly-flap control surface, was conducted with the goal of improving the trimmed maximum-lift coefficient. Tailless aircraft have aerodynamic and structural efficiencies that are superior to those of a traditionally configured wing/body/tail aircraft. However, tailless aircraft have a low maximum-lift coefficient such that; when sized for equivalent takeoff performance, the tailless aircraft suffers a large reduction in aerodynamic and structural efficiencies. A Belly-Flap control surface used in combination with wing trailing edge flaps was tested in a wind tunnel with the goal of achieving a longitudinally trimmed solution at a higher maximum lift coefficient. It was determined that, though the Belly-Flap increases the trimmed lift of the tailless configuration at low angles of attack, the maximum lift coefficient is slightly reduced in relation to the controls neutral configuration.

Indexing (document details)
Advisor: Hefazi, Hamid
Commitee:
School: California State University, Long Beach
School Location: United States -- California
Source: MAI 51/01M(E), Masters Abstracts International
Source Type: DISSERTATION
Subjects: Engineering, Aerospace engineering, Mechanical engineering
Keywords:
Publication Number: 1517618
ISBN: 9781267460202
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