ABOUT METHODS OF DETEMINING BUFFET ONSET BOUNDARY FOR A PASSENGER AIRCRAFT WING

2018 ◽  
Vol 49 (8) ◽  
pp. 809-823
Author(s):  
Nikolay Nikolaevich Bragin
Keyword(s):  
Aircraft Wing ◽  
Passenger Aircraft

scholarly journals An active system for controlling the wing flap flow on a model of a passenger aircraft wing section

2021 ◽  
pp. 41-46
Author(s):  
D. A. Zhogolev ◽  
A. A. Kopylov ◽  
A. A. Nikulenko ◽  
S. Ya. Sevostyanov ◽  
V. G. Sudakov
Keyword(s):  
Active System ◽  
Aircraft Wing ◽  
Wing Section ◽  
Passenger Aircraft

Analysis of Drag for an Aircraft Wing Model with and without Winglet

2011 ◽  
Vol 1 (7) ◽  
pp. 89-91
Author(s):  
Mitul Patel ◽  
◽  
Sharvil Shah ◽  
Dharmendra Dubey
Keyword(s):  
Aircraft Wing ◽  
Wing Model

Identification of the static and dynamic numerical model of a jet aircraft wing from experimental tests

2021 ◽  
Author(s):  
Claudio Chiodi ◽  
Giuliano Coppotelli ◽  
Jacopo Valentino Covioli
Keyword(s):  
Numerical Model ◽  
Experimental Tests ◽  
Aircraft Wing

scholarly journals Design of a Variable-Stiffness Compliant Skin for a Morphing Leading Edge

2021 ◽  
Vol 11 (7) ◽  
pp. 3165
Author(s):  
Zhigang Wang ◽  
Yu Yang
Keyword(s):  
Composite Laminate ◽  
Large Scale ◽  
Design Method ◽  
Leading Edge ◽  
Variable Stiffness ◽  
Manufacturing Constraints ◽  
Aircraft Wing ◽  
Noise Abatement ◽  
Civil Aircraft ◽  
Final Profile

A seamless and smooth morphing leading edge has remarkable potential for noise abatement and drag reduction of civil aircraft. Variable-stiffness compliant skin based on tailored composite laminate is a concept with great potential for morphing leading edge, but the currently proposed methods have difficulty in taking the manufacturing constraints or layup sequence into account during the optimization process. This paper proposes an innovative two-step design method for a variable-stiffness compliant skin of a morphing leading edge, which includes layup optimization and layup adjustment. The combination of these two steps can not only improve the deformation accuracy of the final profile of the compliant skin but also easily and effectively determine the layup sequence of the composite layup. With the design framework, an optimization model is created for a variable-stiffness compliant skin, and an adjustment method for its layups is presented. Finally, the deformed profiles between the directly optimized layups and the adjusted ones are compared to verify its morphing ability and accuracy. The final results demonstrate that the obtained deforming ability and accuracy are suitable for a large-scale aircraft wing.

scholarly journals Gap volume prediction for aircraft wing assembly

2021 ◽  
Vol 54 ◽  
pp. 227-232
Author(s):  
Ye Yang ◽  
Yan Jin ◽  
Mark Price ◽  
Gasser Abdelal ◽  
Paul Maropoulos ◽  
...  
Keyword(s):  
Aircraft Wing
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