Investigation of the flexible missile fins under aerothermal loadings

Download

index.pdf

Date

2018

Author

Özkökdemir, Emir

Metadata

Show full item record

Item Usage Stats

291
views

190
downloads

Wings or fins on the body flying at the supersonic speed are subjected to the aerothermal loading. These loads are categorized into two main groups; aerodynamic pressure and aerodynamic heating. They affect the strength of wings. In this thesis study, a flexible NACA 65-009 wing of a missile flying at supersonic speed is investigated. It is studied to define the effect of the change in wing geometry by the external loads on the flow characteristics. The flow simulations are carried on Ansys Fluent that uses the finite-volume method with the SIMPLE-type fully implicit algorithm to solve the conservation equations. Abaqus Standard is used for simulating the load cases to obtain the structural deformation by using the finite element technique. According to the result of simulations, the effect of deformation at lower supersonic regime (1.2<M<2) is relatively lower but it becomes important when the free stream velocity reaches to Mach number of 2.5 and the difference of aerodynamic performances (drag coefficients) of deformed and undeformed wings is about 8.6 %.

Subject Keywords

Computational fluid dynamics., Aerodynamics., Rockets (Aeronautics).

URI

http://etd.lib.metu.edu.tr/upload/12622283/index.pdf
https://hdl.handle.net/11511/27418

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

Investigation of the Mechanical Integrity of Wings Fins under Thermal Loading Özkökdemir, Emir; Kurtuluş, Dilek Funda (null; 2016-07-15) Wings or fins are exposed to a variety of loading during fight at supersonic and hypersonic regime. Thermal loading is one of the most important loading type is highly effective on the structure of wings/fins. Temperature gradient formed by thermal loading may cause deformation on the wings/fins. Structural integrity of wings/fins under thermal loading as aerodynamic heating were investigated in this work. NACA 0012 airfoil profile was selected as two dimensional analysis models. A set of analysis includes ...
Parametric investigation of hull shaped fuselage for amphibious UAV Sazak, Emre; Kurtuluş, Dilek Funda; Department of Aerospace Engineering (2017) Performance of amphibious unmanned aerial vehicles (UAV’s) that take off from and land on water, like seaplanes, greatly depend on hydrodynamic effects as well as aerodynamic effects, therefore their geometries need to be optimized for both. This study mainly investigates the effect of geometric parameters of a generic, hull-shaped fuselage that are constrained by hydrodynamic drivers, such as the step height needed to reduce hydrodynamic drag, sternpost angle and deadrise angle needed for safe landing; on ...
Parametric investigation of hull shaped fuselage for an amphibious UAV Sazak, Emre; Kurtuluş, Dilek Funda (null; 2016-07-15) Performance of amphibious UAV’s (Unmanned Aerial Vehicles) that take off from and land on water, like seaplanes, greatly depend on hydrodynamic effects as well as aerodynamic effects, therefore their geometries need to be optimized. This study mainly investigates the effect of geometric parameters of a generic, hull-shaped fuselage that are constrained by hydrodynamic drivers, such as the step height needed to reduce hydrodynamic drag, and deadrise and sternpost angles needed for safe landing, on aerodynami...
Aeroelastic Modelling and Testing of a Thin Laminated Composite Missile Fin/Wing Aslan, Göktuğ; Kırımlıoğlu, Serdar; Kurtuluş, Dilek Funda (null; 2017-06-09) Missile fins or wings exposed to different coupled aerodynamic loads during the mission or flight at subsonic and supersonic velocity profile. Aerodynamic loads varying with the angle of attack and the velocity profile may cause some structural fatigue and failure problems. In order to achieve such problems, high strength materials such as composites are required. In this work, a laminated composite missile fin was investigated in terms of the strength varying with the aerodynamic profile. The fiber orienta...
Investigation of missiles with strake fins and reduction of aerodynamic cross coupling effects by optimization Usta, Engin; Tuncer, İsmail Hakkı; Department of Aerospace Engineering (2015) Missiles with very low aspect ratio fins (also called strakes) are generally difficult to model by using engineering level aerodynamic methods and linear theories break due to complex nature of the flow adjacent to the mutual interference of the body and fin. Since fast prediction methods cannot accurately model vortex development along and downstream of very low aspect ratio fins, they have limited success for application to missiles with strake fins. Moreover, there is limited number of CFD studies for in...

Citation Formats

E. Özkökdemir, “Investigation of the flexible missile fins under aerothermal loadings,” M.S. - Master of Science, Middle East Technical University, 2018.