Numerical simulation of lateral jets in supersonic crossflow of missiles using computational fluid dynamics

Download

index.pdf

Date

2019

Author

Dağlı, Efe Can

Metadata

Show full item record

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

Item Usage Stats

131
views

56
downloads

In this thesis, numerical simulation method for modelling lateral jet in supersonic crossflow is presented. Lateral jet control provides high maneuverability to the missile at difficult flow conditions. Besides, jet in a crossflow case has a highly complicated flow domain which should be examined using numerical or experimental methods. In this study, numerical methods are used. The thesis consists of two main sections. In the first section, a validation study is conducted for numerical simulation method using experimental results of a generic missile geometry with lateral jet from literature. First, grid independency and turbulence model studies are conducted for validation model. In the turbulence model study k- Realizable and k- SST turbulence models have been used and results show that, k- Realizable model results in closer results to the experimental data. Moreover, surface pressure distribution data from experiment is used for validating numerical simulation method. Hence, results of the numerical simulation are in a good agreement with the experimental results except for some deviations at the recirculation region. In the second section, a parametric study is conducted for generating a database of jet and crossflow interactions using the validated numerical simulation method. In the parametric study, a slender missile geometry with lateral jet is used. Examined parameters are jet location, jet spouting angle, free-stream and jet flow velocity, and incidence angle. It is seen that, spouting jet normally results in best maneuverability. Furthermore, jet locations result in varying performance depending on the free-stream flow velocity. Once for all, jet flow Mach is inspected and seen that, jet performance depends strongly on jet flow Mach number.

Subject Keywords

Jets, Jets Fluid dynamics., Lateral Thruster, Side Jet, Computational Fluid Dynamics, Fluent.

URI

http://etd.lib.metu.edu.tr/upload/12623328/index.pdf
https://hdl.handle.net/11511/43468

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

Study of jet shapes in inclusive jet production inppcollisions ats=7 TeVusing the ATLAS detector Aad, G.; et. al. (American Physical Society (APS), 2011-3-8) Jet shapes have been measured in inclusive jet production in proton-proton collisions at √ s = 7 TeV using 3 pb − 1 of data recorded by the ATLAS experiment at the LHC. Jets are reconstructed using the anti- k t algorithm with transverse momentum 30 GeV < p T < 600 GeV and rapidity in the region | y | < 2.8 . The data are corrected for detector effects and compared to several leading-order QCD matrix elements plus parton shower Monte Carlo predictions, including different sets of par...
Computational Analysis of a Model Scale Helicopter Rotor in Ground Effect Şahbaz, Mehmet; Sezer Uzol, Nilay; Kurtuluş, Dilek Funda (2017-09-22) In this study, a numerical investigation of ground effect of a helicopter rotor is investigated with Computational Fluid Dynamics method. For this purpose, a model scale 2 bladed helicopter rotor is chosen. An experimental study is referred for comparison and validity of CFD method.
Numerical Simulation of a Flapping Micro Aerial Vehicle Through Wing Deformation Capture Tay, W. B.; de Baar, J. H. S.; Perçin, Mustafa; Deng, S.; van Oudheusden, B. W. (American Institute of Aeronautics and Astronautics (AIAA), 2018-8) Three-dimensional numerical simulations of a four-wing flapping micro aerial vehicle (FMAV) with actual experimentally captured wing membrane kinematics have been performed using an immersed boundary method Navier-Stokes finite volume solver. To successfully simulate the clap and fling motion involving the wing intersection, the numerical solver has been specifically modified to use a newly improved interpolation template searching algorithm to prevent divergence. Reasonable agreement was found between the ...
Computational fluid dynamics simulations of ship airwake Sezer Uzol, Nilay; Sharma, A.; Long, L.N. (2005-10-01) Computational fluid dynamics (CFD) simulations of ship airwakes are discussed in this article. CFD is used to simulate the airwakes of landing helicopter assault (LHA) and landing platform dock-17 (LPD-17) classes of ships. The focus is on capturing the massively separated flow from sharp edges of blunt bodies, while ignoring the viscous effects. A parallel, finite-volume flow solver is used with unstructured grids on full-scale ship models for the CFD calculations. Both steady-state and time-accurate resul...
Numerical and experimental investigation of direct connected ramjet test facility Esirgen, Başar; Aksel, Mehmet Haluk; Ak, Mehmet Ali; Department of Mechanical Engineering (2014) The main objective of this study is to make a numerical model of direct connected ramjet test facility which is used for ground tests of supersonic air breathing propulsion systems. Conceptual design of a direct connected ramjet test facility is performed. 1 dimensional transient numerical model is made according to this conceptual design. Numerical model is made by using 1 dimensional computational fluid dynamic code FLOWNEX. Validation of the numerical model is performed by comparison of test data. After ...

Citation Formats

E. C. Dağlı, “Numerical simulation of lateral jets in supersonic crossflow of missiles using computational fluid dynamics,” Thesis (M.S.) -- Graduate School of Natural and Applied Sciences. Mechanical Engineering., Middle East Technical University, 2019.