Static aeroelastic analysis of supersonic nozzles and performance response

Date

2014-01-01

Author

Duzel, U.
Eyi, Sinan

Metadata

Show full item record

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

Item Usage Stats

176
views

0
downloads

© 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.The effects of static aeroelasticity on the performance of supersonic nozzles are analyzed. A flow analysis was conducted to investigate five different configurations of two dimensional convergingdiverging nozzles. Computational results are validated with experimental data. Two of the configurations, which have the same throat area, throat radius, and convergence angle and total nozzle length are selected as the baseline geometries. By modifying throat radius and keeping all other geometric parameters to be the same, three more configurations are obtained. Flow analyses are performed by using FLUENT, flow solver software. By considering nozzle walls as flexible structure, a static aeroelastic model is implemented to one of the cases. The flexible wall model uses two dimensional linear beam theory. The results of flexible and rigid walls are compared for different supersonic nozzle thicknesses.

URI

https://hdl.handle.net/11511/69561

DOI

https://doi.org/10.2514/6.2014-3689

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Analysis and adjoint design optimization of hypersonic blunt bodies Piskin, Tugba; Eyi, Sinan (2014-01-01) © 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.The main purpose of this study is to analyze hypersonic flow field around the blunt bodies and to design of that bodies in order to obtain minimum pressure drag. Modeling of non-equilibrium must be done properly. In this study, non-equilibriums of thermal and chemical modes are considered. Translational and rotational energy modes are assumed that energy exchange between these modes is so fast. Vibrational and electro...
Analysis and design optimization of three dimensional nozzles Yildizlar, B.; Eyi, Sinan (2014-01-01) © 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.The aim of this study is to develop analysis and design optimization method for three dimensional nozzles. For analysis, three dimensional Euler equations are solved using both Newton and Newton-GMRES methods and their performances are compared. The Jacobian matrix needed for Newton method is evaluated analytically. Newton-GMRES method is a matrix free solution technique hence it does not require the Jacobian matrix e...
Analysis of hypersonic flow using three dimensional Navier-Stokes equations Özgün, Muharrem; Eyi, Sinan (2014-01-01) © 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.The purpose of this study is to develop an accurate and efficient CFD code that can be used in hypersonic flows. The flow analysis is based on the three dimensional Navier-Stokes equations. These equations are solved by using Newton’s method. The analytical method is used to calculate the Jacobian matrix. Flow parameters and convective heat transfer are analyzed on Apollo AS-202 Command Module. Especially, temperature...
Noise prediction of a transonic cavity flow via shear-layer-adapted delayed detached-eddy simulation Yalçın, Özgür; Özyörük, Yusuf (2018-01-01) © 2018 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.An open cavity flow contains a highly turbulent shear layer which separates from the upstream edge and impinges on the aft wall of the cavity, causing intense noise emission. In this study, a delayed detached-eddy simulation (DDES) with the use of "shear-layer-adapted" subgrid length scale, an enhancement of DDES available in literature, is conducted for such an open cavity flow problem. The results show that this len...

Citation Formats

U. Duzel and S. Eyi, “Static aeroelastic analysis of supersonic nozzles and performance response,” 2014, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/69561.