Aerodynamic development of a small horizontal tail for an active control relaxed stability transport application

Urie, D. M.; Reaser, J. S.

doi:10.2514/6.1979-1653

Cited by 2 publications

(2 citation statements)

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“…Relaxed static stability can be achieved by either moving the center of gravity backward [32,61] or by shifting the aerodynamic center forward [31,62]. The more aft center of gravity leads to a smaller trim drag, which can be realized with a shorter fuselage length, like the design utilized in Boeing's transport aircraft, or an extra fuel tank at the rear airframe, like the design utilized in the Concorde supersonic aircraft.…”

Section: Static Stability Marginmentioning

confidence: 99%

“…Firstly, this approach has been applied in research aimed at designing various aircraft configurations. The examples range from civil transport aircraft [30][31][32], conceptual BWB configurations [1,33,34] to other unconventional aircraft [35,36] and some unmanned airplanes [37,38]. Secondly, various achievements have been made in exploring the effects of this technique on the tradeoffs or benefits in terms of aircraft design [1,33,39].…”

Section: Introductionmentioning

confidence: 99%

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Effects of Static Stability Margin on Aerodynamic Design Optimization of Truss-Braced Wing Aircraft

Qiao

et al. 2023

Aerospace

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Currently, the aviation industry is facing an oil and energy crisis and is contributing much more greenhouse gas emissions to the environment. Aircraft design approaches, such as aerodynamic shape optimization, new configuration concepts, and active control technology, have been the primary and effective means of achieving goals concerning fuel burn, noise, and emissions. For now, the design problems of relaxed static stability (RSS, an active control technique) and truss-braced wing (TBW) configurations with high-fidelity aerodynamic shape optimization methods have been investigated widely to promote aerodynamic performance. Nevertheless, they are studied almost always separately, and the combination of exploration and refined design is rarely presented. Therefore, the purposes of this work are to evaluate the benefits of RSS on a full TBW wing–body–tail configuration under various flight conditions and the effects on multi-components and to further explore the potential and analyze the aerodynamic features with the combination of shape optimization and RSS. To address these issues, on the one hand, a range of seven static stability margins are adopted to evaluate its effects with a high-fidelity Reynolds-averaged Navier–Stokes solver. On the other hand, seven cases of drag minimization multipoint aerodynamic design optimization are performed, which are with 600 shape variables and 13 twist variables, subject to lift coefficient, trim, and thickness constraints. The results indicate that with RSS only, the initial configuration has a 2.39% drag reduction under cruise conditions and a 3.01% and a 5.24% drag reduction under two off-design conditions. Additionally, the effects on the multi-components are observed and analyzed. Moreover, all of the optimized configurations with RSS have 2.13%, 2.42%, and 2.12% drag reductions under cruise conditions, drag divergence conditions, and near-buffet-onset conditions, respectively. The most promising optimized configuration has a lift-to-drag ratio of 24.48 with an aerodynamic efficiency of 17.14. The evaluations with a series of off-design points also present high-level aerodynamic efficiency.

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Section: Static Stability Marginmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Effects of Static Stability Margin on Aerodynamic Design Optimization of Truss-Braced Wing Aircraft

Qiao

et al. 2023

Aerospace

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The CADAM^® System for Aircraft Structural Design

Ricci

Smyth

1980

SAE Technical Paper Series

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Aerodynamic development of a small horizontal tail for an active control relaxed stability transport application

Cited by 2 publications

References 1 publication

Effects of Static Stability Margin on Aerodynamic Design Optimization of Truss-Braced Wing Aircraft

Effects of Static Stability Margin on Aerodynamic Design Optimization of Truss-Braced Wing Aircraft

The CADAM^® System for Aircraft Structural Design

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Aerodynamic development of a small horizontal tail for an active control relaxed stability transport application

Cited by 2 publications

References 1 publication

Effects of Static Stability Margin on Aerodynamic Design Optimization of Truss-Braced Wing Aircraft

Effects of Static Stability Margin on Aerodynamic Design Optimization of Truss-Braced Wing Aircraft

The CADAM® System for Aircraft Structural Design

Contact Info

Product

Resources

About

The CADAM^® System for Aircraft Structural Design