Aeroelastic Model Corrections of a Very Light Aircraft; Implications on Static Trim, Flutter and Gust Response

Date

2022-01-01

Author

Demirer, Halime Gül
Kayran, Altan

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

142
views

0
downloads

© 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.This paper discusses the aeroelastic model corrections employed in the static and dynamic aeroelastic analysis of a very light aircraft. MSC.FlightLoads and MSC.Nastran are used for aeroelastic modeling and analysis. Discussion covers improvement of the aerodynamic solution, aerodynamic modeling approaches and aero-structure coupling alternatives. Aerodynamic calculations are based on the Doublet-Lattice Method (DLM). The aerodynamic solution is improved by including the camber and the angle of incidence of the wing through the addition of initial downwash. DLM-based loads are compared with loads obtained from computational fluid dynamics (CFD) analysis. Additionally, the effect of actuator stiffness is discussed, and different aeroelastic modeling alternatives, such as connecting the wings with a lifting panel, whether or not to couple the wing-bridging plate with the structural model are compared. The effects of aeroelastic model corrections on static trim, flutter and gust response solutions are investigated.

URI

https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85135039548&origin=inward
https://hdl.handle.net/11511/99124

DOI

https://doi.org/10.2514/6.2022-3597

Conference Name

AIAA AVIATION 2022 Forum

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Parametric design and investigation of grid fin aerodynamics in supersonic flow using computational fluid dynamics Dinçer, Erdem; Sezer Uzol, Nilay (2022-01-01) © 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.Recently, with the advances in modern missile industry, faster and more maneuverable missiles became fashionable. Designing fast and agile missiles requires efficient and strong control surfaces and grid fin is a candidate to fulfill this need. Grid fins are unconventional control surfaces, which has an outer frame supporting interior web structure. In this paper, “MICOM Grid Fin” wind tunnel experiments are used as th...
Adjoint based design optimization of subsonic airfoils using a panel code together with a rans solver Sarikaya, Berk; Tuncer, İsmail Hakkı (2022-01-01) © 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.The automatic differentiation tool, FDOT, is employed to perform sensitivity analyses on an in-house panel code. Sensitivity derivatives obtained are then used for aerodynamic shape optimization of airfoil profiles. A baseline airfoil is optimized with the panel code for the target lift and moment coefficients while minimizing the adverse pressure gradient on the airfoil. Airfoil profiles are parametrized by the Class ...
Aerodynamic optimization of wing-body configuration using discrete adjoint method Yıldırım, Ahmet; Eyi, Sinan (2017-01-01) © 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.The gradient based sensitivities required by design optimization are obtained by three different methods based on three dimensional Euler equations. Finite difference, Direct and Adjoint methods are used to compute objective sensitivities. A cell centered, upwind based finite volume method is implemented to discretize the Euler equations. The flow solution is obtained by preconditioned matrix-free Newton-GMRES algorith...
Aerothermodynamic design optimization in hypersonic flows Eyi, Sinan (2013-01-01) © 2013, American Institute of Aeronautics and Astronautics Inc. All rights reserved.The objective of this study is to develop a reliable and efficient design tool that can be used in hypersonic flows. The flow analysis is based on the axisymmetric Euler and the finite rate chemical reaction equations. These coupled equations are solved by using Newton’s method. The analytical and numerical methods are used to calculate Jacobian matrices. The effects of error in numerical Jacobians on the performance of flow...
Experimental design and statistical modeling methodology for wind tunnel aerodynamics of an agile missile to improve the simulation accuracy and performance Savas, Ozgun; Topbas, Eren; Unal, Kenan; Karaca, H. Deniz; Kutay, Ali Türker (2018-01-01) © 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.Wind tunnel testing is an essential procedure to investigate the aerodynamics forces and moments. In this paper, a methodology is presented to perform such test in an efficient way. Experimental design process is carried out before the testing in order to cover the flight regime as much as possible with the least possible number of tests. After the determination of the test matrix and conducting the wind-on tests, the ...

Citation Formats

H. G. Demirer and A. Kayran, “Aeroelastic Model Corrections of a Very Light Aircraft; Implications on Static Trim, Flutter and Gust Response,” presented at the AIAA AVIATION 2022 Forum, Illinois, Amerika Birleşik Devletleri, 2022, Accessed: 00, 2022. [Online]. Available: https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85135039548&origin=inward.