Fully transient conjugate analysis of silica-phenolic charing ablation coupled with interior ballistics

Date

2019-01-01

Author

Alanyalıoğlu, Çetin Ozan
Özyörük, Yusuf

Metadata

Show full item record

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

Item Usage Stats

256
views

0
downloads

© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.Due to its excellent insulation capability, usage of silica-phenolic charring ablator as nozzle liner is a common practice in solid rocket motor industry. During the design of a solid rocket motor employing silica-phenolic as nozzle liner, it is desired to conduct an accurate analysis yielding in-depth thermal response and recession characteristics. As the interior ballistics and nozzle recession rate mutually interact, best practice is to perform a coupled solution to both. Commonly used one-dimensional analysis tools with empirical approaches for estimation of convective heat transfer rate and blowing effect generally lack sought accuracy, and do not model the transient shape-change phenomena, which affects the nozzle performance. This work provides governing equations for charring, including pyrolysis gas injection and surface energy balance for melting ablation, along with a boundary condition governed by interior ballistics, and implements all these numerically into the commercial CFD solver FLUENT. Also, results from a static firing test conducted with a small scale ballistic evaluation motor employing a silica-phenolic nozzle insert are provided. Results from both investigations are compared and discussed. It is demonstrated that the implementation captures all the relevant physical phenomena.

URI

https://hdl.handle.net/11511/69330

DOI

https://doi.org/10.2514/6.2019-3958

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

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...
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 ...
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...
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 ...
High strain rate material characterization of Al 7075-T651 by modified Taylor impact test and velocity interferometry Kesemen, Latif; Kayran, Altan (2017-01-01) © 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.Metallic materials in aerospace structures are exposed to impact loading depending on their usage area. High strain rate material characterization of metallic materials is very crucial to properly prepare finite element models to be used in impact loading situations. Aluminum alloys are widely used in aerospace structures in variety of areas. Johnson-Cook material model is a suitable material model to represent the beh...

Citation Formats

Ç. O. Alanyalıoğlu and Y. Özyörük, “Fully transient conjugate analysis of silica-phenolic charing ablation coupled with interior ballistics,” 2019, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/69330.