Termal Yüklere Maruz Kalan Naca 0012 Kanat Yapisinin İncelenmesi

Date

2016-10-14

Author

Özkökdemir, Emir
Acar, B
Kurtuluş, Dilek Funda

Metadata

Show full item record

Item Usage Stats

262
views

0
downloads

Süpersonik rejimde uçan kanatlar çeşitli yüklemelere maruz kalırlar. Bu yükleme tiplerinden biri olan termal yüklemeler, kanatların tasarımı üzerinde oldukça etkilidir, bu nedenle büyük öneme sahiptir. Termal yükleme kaynaklı oluşan termal gradyan kanatlar üzerinde yapısal bozulmalara yol açabilir. Bu çalışmanın amacı aerodinamik ısınma gibi termal yüklemelere maruz kalan kanatların yapısal bütünlüğü incelenmesidir. 2 boyutlu olarak yapılan karşılaştırma analizleri için literatürde bulunan NACA0012 kanat profili seçilmiştir. Hesaplamalı akışkanlar dinamiği ve sonlu elemanlar modelleri ayrı ayrı oluşturulmuş, elde edilen sonuçlar literatür verileri ile karşılaştırılmıştır.

Subject Keywords

Wing, Canard, Aerodynamic Heating, Computational Fluid Dynamics(CFD), Finite Element Methods (FEM)

URI

https://hdl.handle.net/11511/71132

Conference Name

8. Savunma Teknolojileri Kongresi , SAVTEK, 12 - 14 Ekim 2016

Collections

Department of Aerospace Engineering, Conference / Seminar

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 ...
Investigation of the flexible missile fins under aerothermal loadings Özkökdemir, Emir; Kurtuluş, Dilek Funda; Department of Aerospace Engineering (2018) 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...
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 ...
Effect of ground on flow structure of non-slender delta and reverse delta wings Koçak, Göktuğ; Yavuz, Mehmet Metin; Department of Mechanical Engineering (2023-1-26) Flight condition of aircrafts proximity to the ground, so-called “Ground Effect” (GE), is among one of the most recent research areas since the aerodynamic performance and stability of wing in ground effect (WIG) crafts significantly vary due to the flow dynamics associated with the interaction between the wing and the surface. In the present study, ground effect of non-slender delta wings (DW) and reversed delta wings (RDW) at static ground effect (SGE) condition in the absence of heave and pitch motion w...
Development and evaluation of new bleed boundary condition models for supersonic inlet boundary layer bleed flow Akar, Gökhan; Eyi, Sinan; Department of Aerospace Engineering (2019) Shock wave/boundary layer interaction is an important issue that should be considered when studying supersonic inlet design for air vehicles. Porous bleed systems have traditionally been used for increase stability and efficiency of the supersonic inlets by means of removing the lower momentum part of the boundary layer to prevent flow separation caused by adverse pressure gradient. However, evaluating and determining the effect of the boundary layer bleed system on the performance of the supersonic inlet i...

Citation Formats

E. Özkökdemir, B. Acar, and D. F. Kurtuluş, “ Termal Yüklere Maruz Kalan Naca 0012 Kanat Yapisinin İncelenmesi,” presented at the 8. Savunma Teknolojileri Kongresi , SAVTEK, 12 - 14 Ekim 2016, Ankara, Türkiye, 2016, Accessed: 00, 2021. [Online]. Available: https://hdl.handle.net/11511/71132.