Qiao et al 2024a - Revision history

Scipediacontent at 09:19, 30 June 2025

2025-06-30T09:19:05Z

Scipediacontent at 09:06, 30 June 2025

2025-06-30T09:06:11Z

Scipediacontent at 09:04, 30 June 2025

2025-06-30T09:04:12Z

Onate: Onate moved page Review 457822922104 to Qiao et al 2024a

2024-12-09T09:22:27Z

Onate moved page Review 457822922104 to Qiao et al 2024a

JSanchez: JSanchez moved page Draft Sanchez Pinedo 547815686 to Review 457822922104

2024-12-05T10:26:08Z

JSanchez moved page Draft Sanchez Pinedo 547815686 to Review 457822922104

JSanchez: Created page with " == Abstract == The bending and torsional stiffness influence structural deformation to varying degrees. Utilizing the coupled numerical method of Computational Fluid Dynamic..."

2024-12-05T10:26:05Z

Created page with " == Abstract == The bending and torsional stiffness influence structural deformation to varying degrees. Utilizing the coupled numerical method of Computational Fluid Dynamic..."

New page

== Abstract ==

The bending and torsional stiffness influence structural deformation to varying degrees. Utilizing the coupled numerical method of Computational Fluid Dynamics and Computational Structural Dynamics (CFD/CSD), a comprehensive study was conducted on the impact of bending and torsional stiffness on the static aeroelastic behavior of a high-aspect-ratio wing, employing FLUENT software across diverse flight conditions. The study summarized this influence by comparing the computational outcomes. The results indicate that as the angle of attack rises, the lift increment diminishes gradually until the angle reaches 14 degrees, rendering the strategy of enhancing bending and torsional stiffness to gain more lift ineffective. Between 2 and 14 degrees of angle of attack, the lift difference between the scenarios decreases from 23.98% to 7.31%. At higher Mach numbers and lower angles of attack, augmenting wing stiffness significantly boosts wing lift. Optimal lift-to-drag characteristics are achieved at approximately 6 degrees of angle of attack. By averagely increasing the wing’s bending and torsional stiffness by 8.28% and 5.22%, respectively, the lift-to-drag characteristics can be enhanced by 5.27% at a low angle of attack of 0.75 Mach. The disparity in maximum deflection between the two stiffness wings is most pronounced at higher flight speeds and smaller angles of attack, with the opposite trend observed for the difference in maximum torsion angle. The key findings presented in this paper can expedite the integrated design of stiffness for this type of wing structure by providing vital technical insights.OPEN ACCESS Received: 24/07/2024 Accepted: 22/10/2024

== Full document ==
<pdf>Media:Draft_Sanchez Pinedo_547815686-1373-document.pdf</pdf>

← Older revision		Revision as of 09:19, 30 June 2025
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	== Full document ==		== Full document ==
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← Older revision		Revision as of 09:04, 30 June 2025
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	== Full document ==		== Full document ==
−	<pdf>Media:~~Draft_Sanchez Pinedo_547815686~~-~~1373-document~~.pdf</pdf>	+	<pdf>Media:Qiao_et_al_2024a_5878_12-TSP_RIMNI_56530.pdf</pdf>

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 == Abstract ==
-The bending and torsional stiffness influence structural deformation to varying degrees. Utilizing the coupled numerical method of Computational Fluid Dynamics and Computational Structural Dynamics (CFD/CSD), a comprehensive study was conducted on the impact of bending and torsional stiffness on the static aeroelastic behavior of a high-aspect-ratio wing, employing FLUENT software across diverse flight conditions. The study summarized this influence by comparing the computational outcomes. The results indicate that as the angle of attack rises, the lift increment diminishes gradually until the angle reaches 14 degrees, rendering the strategy of enhancing bending and torsional stiffness to gain more lift ineffective. Between 2 and 14 degrees of angle of attack, the lift difference between the scenarios decreases from 23.98% to 7.31%. At higher Mach numbers and lower angles of attack, augmenting wing stiffness significantly boosts wing lift. Optimal lift-to-drag characteristics are achieved at approximately 6 degrees of angle of attack. By averagely increasing the wing’s bending and torsional stiffness by 8.28% and 5.22%, respectively, the lift-to-drag characteristics can be enhanced by 5.27% at a low angle of attack of 0.75 Mach. The disparity in maximum deflection between the two stiffness wings is most pronounced at higher flight speeds and smaller angles of attack, with the opposite trend observed for the difference in maximum torsion angle. The key findings presented in this paper can expedite the integrated design of stiffness for this type of wing structure by providing vital technical insights.OPEN ACCESS Received: 24/07/2024 Accepted: 22/10/2024
+The bending and torsional stiffness influence structural deformation to varying degrees. Utilizing the coupled numerical method of Computational Fluid Dynamics and Computational Structural Dynamics (CFD/CSD), a comprehensive study was conducted on the impact of bending and torsional stiffness on the static aeroelastic behavior of a high-aspect-ratio wing, employing FLUENT software across diverse flight conditions. The study summarized this influence by comparing the computational outcomes. The results indicate that as the angle of attack rises, the lift increment diminishes gradually until the angle reaches 14 degrees, rendering the strategy of enhancing bending and torsional stiffness to gain more lift ineffective. Between 2 and 14 degrees of angle of attack, the lift difference between the scenarios decreases from 23.98% to 7.31%. At higher Mach numbers and lower angles of attack, augmenting wing stiffness significantly boosts wing lift. Optimal lift-to-drag characteristics are achieved at approximately 6 degrees of angle of attack. By averagely increasing the wing’s bending and torsional stiffness by 8.28% and 5.22%, respectively, the lift-to-drag characteristics can be enhanced by 5.27% at a low angle of attack of 0.75 Mach. The disparity in maximum deflection between the two stiffness wings is most pronounced at higher flight speeds and smaller angles of attack, with the opposite trend observed for the difference in maximum torsion angle. The key findings presented in this paper can expedite the integrated design of stiffness for this type of wing structure by providing vital technical insights.
 == Full document ==
 <pdf>Media:Qiao_et_al_2024a_5878_12-TSP_RIMNI_56530.pdf</pdf>

← Older revision	Revision as of 09:22, 9 December 2024
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← Older revision	Revision as of 10:26, 5 December 2024
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