Parametric design and investigation of grid fin aerodynamics in supersonic flow using computational fluid dynamics

Date

2022-01-01

Author

Dinçer, Erdem
Sezer Uzol, Nilay

Metadata

Show full item record

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

Item Usage Stats

172
views

0
downloads

© 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 the test case to validate the CFD analysis. To perform a parametric study, several grid fin geometries are investigated at Mach number of 2.5 and four different angles of attack ranging from 0° to 15° and two roll angles of 0° and 45°. A parametric design study is performed with chord, span, width, gap between members, web thickness and frame thickness parameters using Box-Behnken DOE methodology. The objective of this study is to create and validate response surfaces for grid fin aerodynamic coefficients using the CFD results. Good agreement is achieved estimating the aerodynamic coefficients with response surfaces except the pitch moment coefficient. Flow field investigations showed that separated flow is occurred at 15° angle of attack resulting in moderate agreement in pitch moment.

URI

https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85135382967&origin=inward
https://hdl.handle.net/11511/99954

DOI

https://doi.org/10.2514/6.2022-3387

Conference Name

AIAA AVIATION 2022 Forum

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Aeroelastic Model Corrections of a Very Light Aircraft; Implications on Static Trim, Flutter and Gust Response Demirer, Halime Gül; Kayran, Altan (2022-01-01) © 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). ...
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 ...
Adjoint Based Shape Optimization of an S-Shaped Duct with SU2 Kucuk, Umut Can; Tuncer, İsmail Hakkı (2022-01-01) © 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.In this study, an adjoint based aerodynamic shape optimization of an intake duct is performed for a set of objectives. The objectives include the minimization of total pressure loss, the minimization of total pressure loss constrained with the minimum mass flow rate and the maximization of mass flow rate. M2129 intake duct is taken as the baseline geometry. The Flow and the adjoint solutions are obtained with the open ...
Computational fluid dynamics and proper orthogonal decomposition based control of flow over supersonic cavities Gelisli, Kubra Asena; Aradag, Selin; Tascioglu, Yigit; Özer, Mehmet Bülent (2019-01-01) © 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.A Computational Fluid Dynamics (CFD) study is conducted to investigate the unsteady, turbulent supersonic cavity flow characteristics and to control the severe effects of the flow field. Simulations of Mach 1.5 supersonic cavity flow with a length to depth ratio of 5.07 are performed using commercial ANSYS Fluent solver. Unsteady density-based Reynolds Averaged Navier-Stokes equations are modeled with standard k-ω turb...
Computational modelling and analysis of porous bleed holes at supersonic speeds Akar, Gökhan; Eyi, Sinan (2020-01-01) © 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.Shock Wave / Boundary Layer Interaction is an important issue that should be taken into account when studying inlet design. Bleed holes have traditionally been used to remove the lower momentum part of the boundary layer to avoid separation from adverse Shock Wave / Boundary Layer Interaction. In this study, modeling of porous bleed holes investigated in computational fluid dynamics on a flat plate with and without an ...

Citation Formats

E. Dinçer and N. Sezer Uzol, “Parametric design and investigation of grid fin aerodynamics in supersonic flow using computational fluid dynamics,” 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=85135382967&origin=inward.