Show/Hide Menu
Hide/Show Apps
Logout
Türkçe
Türkçe
Search
Search
Login
Login
OpenMETU
OpenMETU
About
About
Open Science Policy
Open Science Policy
Open Access Guideline
Open Access Guideline
Postgraduate Thesis Guideline
Postgraduate Thesis Guideline
Communities & Collections
Communities & Collections
Help
Help
Frequently Asked Questions
Frequently Asked Questions
Guides
Guides
Thesis submission
Thesis submission
MS without thesis term project submission
MS without thesis term project submission
Publication submission with DOI
Publication submission with DOI
Publication submission
Publication submission
Supporting Information
Supporting Information
General Information
General Information
Copyright, Embargo and License
Copyright, Embargo and License
Contact us
Contact us
Scaling for icing wind tunnel tests andvalidation with numerical simulations
Download
index.pdf
Date
2019
Author
Özbek Yanmaz, Gizem.
Metadata
Show full item record
This work is licensed under a
Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License
.
Item Usage Stats
230
views
143
downloads
Cite This
Icing is one of the most dangerous hazards to be encountered by air vehicles in flight. Ice accretion, particularly on control surfaces, wings and flight data sensors usually degrades both performance and operational safety of air vehicles. Thus, it has become important in the design and certification phases of system development to evaluate performance degradation because of icing. Icing wind tunnel testing is the most convenient method considering feasibility, cost and safety. However, when full-size model is too large for a given facility or when the desired test conditions are out of the operating capability of the facility, a scaling method that produces scaled ice accretions over a wide range of test conditions and that can be applied to a variety of icing testing situations is needed. The scaling method shall be validated before the icing wind tunnel testing for reliability and validity of the tests. This work illustrates a scaling method for size scaling and test-condition scaling that is based on similitudes of geometry, flow field, droplet trajectory, water catch, energy balance and surface water dynamics. Icing analyses are performed for full-size and scaled conditions using an in-house icing code AEROMSICE-2D and a CFD tool ANSYS® Fluent 18.0 and in-flight icing code FENSAP-ICE. The ice accretions obtained by analyses are verified with experimental data available in the literature. Furthermore, the scaling method is tested for geometry scaling and velocity scaling at several icing conditions.
Subject Keywords
Flight.
,
Keywords: In-flight Icing
,
Icing Scaling
,
Icing Similitude
,
Icing Simulations
,
Icing Test Condition Scaling.
URI
http://etd.lib.metu.edu.tr/upload/12624340/index.pdf
https://hdl.handle.net/11511/44672
Collections
Graduate School of Natural and Applied Sciences, Thesis
Suggestions
OpenMETU
Core
Stability of parallel non-newtonian flows
Özgen, Serkan (1997-01-01)
De-/anti-icing fluids are sprayed on aircraft wings to prevent dangerous loss of performance due to ice formation. The residual layers of such fluids which may either be of newtonian or non-newtonian character could also adversely effect the performance of the aircraft. Therefore it is important to investigate the stability characteristics of such fluids. Stability problem for non-newtonian fluids (power-law fluids in particular) has been solved using the linear stability theory for nearly parallel flows.
Root Cause Analysis of Air France Flight 447 Accident (1 June 2009)
Azık Özkan, Derya; Özkan, Türker (2019-07-05)
Air accidents are extremely rare events and aviation is the safest mode of transportation. On the other hand, the risk is always present whenever any flights take place (Janic, 2000). Therefore, even identifying the main causes of one accident could be very critical for preventing future crashes that could occur at any point and any time. Therefore, the aim of this study is to investigate the root causes of one of the deadliest accidents in the history of Air France that 228 occupants including the crew and...
Experimental Investigation of Optimal Gap Distance between Rotors of a Quadrotor UAV
Kaya, Dilber Derya; Kutay, Ali Türker; Tekinalp, Ozan (2017-06-09)
The effect of spacing between the rotors of a quadrotor Unmanned Aerial Vehicle (UAV) in hovering flight is investigated. Experiments are conducted to obtain a mathematical relation between the diameter of the rotor and gap distance between each rotor. Constraints such as the maximum thrust force and minimum energy consumption are imposed. Several rotors having different sizes are tested at various RPMs with a changing gap distances, and total thrust produced by four rotors is measured. The results are give...
Production and development of de/anti icing fluids for aircraft
Erdoğan, Barış; Uludağ, Yusuf; Department of Chemical Engineering (2008)
Aircraft are not allowed to take off prior to cleaning of snow and ice deposits that form on their surfaces under winter conditions to refrain from compromising flight safety. Water based solutions containing mainly ethylene or propylene glycol, or both, are employed either to remove the snow/ice layers or to provide protection against deposition of these layers. The first group of solutions, i.e. de-icing fluids, are Newtonian and have generally low viscosity so that right after their application they fall...
Steady-State CFD Analysis of 3D Bio-inspired Flapping Wing Models
Bektaş, Mürvet; Kurtuluş, Dilek Funda; Güler, Mehmet Ali (2018-07-11)
The aerodynamics of insects flying at low Reynolds numbers is considered for Micro Air Vehicles (MAV) designs. The aim of this study is to analyze different flapping wing models and to predict generated forces and vortices around the wings. The analyses are significant for understanding properties of flying animals like birds, insects and for improving MAVs more. For three insect species (namely, bumblebee, hawkmoth, and hummingbird), three dimensional (3D) wing models are numerically analyzed at different ...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
G. Özbek Yanmaz, “Scaling for icing wind tunnel tests andvalidation with numerical simulations,” Thesis (M.S.) -- Graduate School of Natural and Applied Sciences. Aerospace Engineering., Middle East Technical University, 2019.