Experimental and Theoretical Study on Aeroelastic Response of High-Aspect-Ratio Wings

AIAA Journal ◽  
2001 ◽  
Vol 39 (8) ◽  
pp. 1430-1441 ◽  
Author(s):  
Deman Tang ◽  
Earl H. Dowell
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Theoretical Study ◽  
Aeroelastic Response

scholarly journals An overview of methods for investigation of aeroelastic response on high aspect ratio fixed-winged aircraft

2020 ◽  
Vol 899 ◽  
pp. 012002
Author(s):  
Muhammad Khizer Ali Khan ◽  
Ali Javed ◽  
Nafees Mumtaz Qadri ◽  
Mohtasshim Mansoor ◽  
Farrukh Mazhar
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Aeroelastic Response

Experimental and Theoretical Study of Gust Response for High-Aspect-Ratio Wing

AIAA Journal ◽  
2002 ◽  
Vol 40 (3) ◽  
pp. 419-429 ◽  
Author(s):  
Deman Tang ◽  
Earl H. Dowell
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Theoretical Study ◽  
Gust Response

Investigation of Computational Non-Linear Aeroelastic Response of High Aspect Ratio Wing

2013 ◽  
Vol 419 ◽  
pp. 55-61
Author(s):  
Hammad Rahman ◽  
Min Li
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Parametric Design ◽  
Aerodynamic Load ◽  
Linear Deformation ◽  
Aeroelastic Response ◽  
Simplified Approach ◽  
Strip Theory ◽  
Non Linear ◽  
The Impact

Aircrafts with high aspect ratio wings are most eligible candidates for high altitude and long endurance flights. Such wings show a non-linear deformation behavior because of structural geometric non-linearity. In the present study both linear and non-linear static aeroelastic behaviors of a high aspect ratio rectangular flat plate wing are analyzed using a simplified approach. The main emphasis lies in the tremendous change of lift distribution on the flexible high aspect ratio wing when large deflections are incorporated in the static aeroelastic analysis. The computational static aeroelastic simulations are performed in the finite element method based commercial software ANSYS-14. The aerodynamic load is calculated using the strip theory. Since the aero-load changes with the twisting deformation hence a user defined script is written using ANSYS parametric design language (APDL). The computationally achieved divergence velocity results are compared with the analytical results. The results of parametric study at different flight load conditions and angles of attack have highlighted the role of geometric nonlinearities in both bending and twisting deformations. The impact of follower pressure forces on the aeroelastic response is also investigated.

RESEARCH MODEL DESIGN FOR NUMERICAL-EXPERIMENTAL STUDY OF HIGH ASPECT RATIO WING AEROELASTIC RESPONSE

2017 ◽  
Author(s):  
Diego Paes de Andrade Peña ◽  
Raimundo Duarte ◽  
ROBERTO GIL ANNES DA SILVA ◽  
Orlando Tomaz da Silva Neto
Keyword(s):  
Experimental Study ◽  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Model Design ◽  
Research Model ◽  
Aeroelastic Response
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