Aerodynamics and Fluid Mechanics Commons^™

Editorial, Maruthupandiyan K Dr.

Graduate Research in Engineering and Technology (GRET)

The aeronautical engineer is responsible for using cost-effective methods to develop ways of improving fuel efficiency and flight safety. Additionally, aeronautical engineers focus on lowering the environmental impact of air travel by creating aircraft that are more environmentally friendly. In Indian scenario, the development of aeronautical related advance technologies is still to grow with the Government of India initiative for the defence product under the Atmanirbhar Bharat and hope in few years now, these advanced technologies will be booming.

Influence Of Wing Planform Shape On The Effectiveness Of A Fixed-Slot, Yuan Zhao

Doctoral Dissertations and Master's Theses

This thesis report explores the effect of the Clark-Y wing geometry on lift and drag to use as a reference during aircraft design stage. The different characteristics investigated are fixed slot span, taper ratio, washout, and sweep angle. Plain wings, half slotted wings, and fully slotted wings were built in CATIA with an aspect ratio of 6 and different taper ratio, washout, and sweep angles. Using the CATIA models to generate the 3-D grids in Pointwise. All the simulations were tested in Ansys-Fluent under sea-level conditions with a Reynold number of 609000. The relationships between the aerodynamic characteristics and the …

Time-Resolved Piv Measurements Of Ship Airwakes With Quartering Winds, Kaijus H. Palm

Doctoral Dissertations and Master's Theses

The unsteady, three-dimensional, turbulent airwake over the Simple Frigate Ship No. 2 (SFS2) with quartering wind flow directions was studied in a low-speed wind tunnel facility. Surface oil flow visualization and time-resolved stereoscopic and planar particle image velocimetry (PIV) measurements were made for three crosswise planes and a single centerline streamwise plane. Measurements included various configurations with the bow of the ship model at two different quartering wind conditions of 10 and 20 degrees, as well as cases with and without the effects of a simulated atmospheric boundary layer (ABL). A comparative analysis of the time-averaged flow structures between the …

Moving Polygon Methods For Incompressible Fluid Dynamics, Chris Chartrand

Doctoral Dissertations

Hybrid particle-mesh numerical approaches are proposed to solve incompressible fluid flows. The methods discussed in this work consist of a collection of particles each wrapped in their own polygon mesh cell, which then move through the domain as the flow evolves. Variables such as pressure, velocity, mass, and momentum are located either on the mesh or on the particles themselves, depending on the specific algorithm described, and each will be shown to have its own advantages and disadvantages. This work explores what is required to obtain local conservation of mass, momentum, and convergence for the velocity and pressure in a …

Characterizing Wake Roll-Up And Vortex Structure For Delta Wing Configuations Featuring Flow Control Devices At Low Reynolds Number, Jeffrey M. Layng

Theses and Dissertations

Various configurations of a cropped delta wing featuring a NACA 0012 wing-section were evaluated experimentally at a Reynolds number of 5.0 x 10⁵ in the Air Force Institute of Technology Low-Speed Wind Tunnel facility. The effects of active flow control (AFC) and passive boundary-layer fences (BLF) were shown to improve high angle of attack delta wing performance. The AFC BLFs were shown to replicate the performance enhancements found in passive BLFs without incurring a drag penalty. An experimental characterization of the wake region is presented to compare the wake roll-up and leading edge vortices for these baseline, passive BLF, …

Exploratory Measurement Of Recession Rates Of Low Temperature Ablators Subjected To Mach 6 Flow, Ross H. Kellet

Theses and Dissertations

The high speed/high-temperature effect of heat shield ablation was simulated in the low-enthalpy AFRL Mach 6 Ludwieg Tube using solid dry ice as a low-temperature sublimator. The experiments utilized both 21 half-angle cones and bi-conic models with a 7 ° half-angle leading edge followed by a 26° half-angle base contained within a cryogenic-cooled stainless steel holder. A method of fabricating dry ice test articles was developed using commercially procured dry ice and custom-made aluminum molds. Tests were performed at Mach 6.1 with a stagnation temperature of 490 K and stagnation pressures ranging from 40 - 500 psi. Unit Reynolds number …

Aeroelastic Analysis Of Small-Scale Aircraft, Kent Roberts

Master's Theses

The structural design of flight vehicles is a balancing act between maximizing loading capability while minimizing weight. An engineer must consider not only the classical static structural yielding failure of a vehicle, but a variety of ways in which structural deformations can in turn, affect the loading conditions driving those deformations. Lift redistribution, divergence, and flutter are exactly such dynamic aeroelastic phenomena that must be properly characterized during the design of a vehicle; to do otherwise is to risk catastrophe. Relevant within the university context is the design of small-scale aircraft for student projects and of particular consideration, the DBF …

A Computational Fluid Dynamics-Based Surrogate Wind Turbine Blade Aerodynamic Model For Hybrid Simulation, Eric Lalonde

Electronic Thesis and Dissertation Repository

Hybrid simulation (HS) is a promising technique for studying wind turbines due to the presence of scaling errors in wind tunnel testing. However, HS of wind-loaded structures is limited by the current practice of using lower-accuracy, "pre-calculated" aerodynamic loads, which uncouple the aerodynamic loading from the structural response. This thesis presents six stand-alone studies that collectively build towards a novel HS framework that employs a computational fluid dynamics (CFD) based surrogate model to generate higher-accuracy aerodynamic loads within the HS loop. An experimentally-validated residential wind turbine model equipped with an external damping system was used to illustrate the proposed framework. …

Detailed Velocity And Heat Transfer Measurements In An Advanced Gas Turbine Vane Insert Using Magnetic Resonance Velocimetry And Infrared Thermometry, Michael Benson, David Bindon Cdt'19, Mattias Cooper Cdt'19, F. Todd Davidson, Benjamin Duhaime Cdt'19, David Helmer, Robert Woodings Cdt'19, Bret P. Van Poppel, Christopher J. Elkins, John P. Clark

West Point Research Papers

This work reports the results of paired experiments for a complex internal cooling flow within a gas turbine vane using magnetic resonance velocimetry (MRV) and steady-state infrared (IR) thermometry. A scaled model of the leading edge insert for a gas turbine vane with multi-pass impingement was designed, built using stereolithography fabrication methods, and tested using MRV techniques to collect a three-dimensional, three-component velocity field data set for a fully turbulent test case. Stagnation and recirculation zones were identified and assessed in terms of impact on potential cooling performance. A paired experiment employed an IR camera to measure the temperature profile …

Characterization, Design, And Optimization Of Dual-Purpose Wind Turbines And Frost Protection Fans, Ethan Narad

Master's Theses

This thesis report outlines the creation of a MATLAB tool to design reversible machines that can function as both wind turbines and as agricultural frost protection fans. Frost protection fans are used to prevent crop loss during radiative freeze events during which a temperature inversion is present. Such a dual-purpose machine fundamentally has the constraint that it must use symmetric airfoils, so a suite of tools for automatically designing an optimized wind turbine blade with symmetric airfoils using the Blade Element Momentum (BEM) theory approach is presented. The BEM code is then re-derived and adapted for use with a frost …

Conceptual Design Of Blended Wing Body For Future Air Transportation, Shruti Dipak Jadhav Er, Pawan Hiteshbhai Jethwa Er, Shiva Prasad U Asst. Prof, Suresh Kumar M Prof.

Graduate Research in Engineering and Technology (GRET)

Blended wing body is a fixed wing aircraft which are smoothly blended together with no clear dividing line and no distinct wings also be given a wide Aerofoil shaped body. The future transportation is of aircrafts will incline towards the aerodynamically efficient and capable of carrying large number of passengers over long range and environmental benefits is the main paradigm in the design of aircraft BWB has a high lift to drag ratio which increases the C_L max and velocity of the airplane with high load factor and high economy compared with traditional aircraft. Evacuation pressure or the cabin …

Aerodynamic Analysis Of An Arrow With Different Fletch Configurations: A Computational Approach, Haricharan Pippari, Harshith Raj Tangutoori, Hemanth Vakati, Sravani Madhurakavi

Graduate Research in Engineering and Technology (GRET)

Archery is being contemplated from hundreds of years; however there have been not many investigations expressing and clarifying the optimal design and aerodynamic effectiveness of an Arrow. Presently Archery has turned into a significant game in Olympics. Every nation is showing colossal interest in delivering champions. So, it is important to work on the solidness of the Arrow to such an extent that its precision and aerodynamic characteristics improve. Broad examination is proceeding to work on the streamlined exhibition of the Arrow. So, this study intends to explore the aerodynamic characteristics of an Arrow for various fletches and diverse Arrow …

Three-Dimensional Flow Analysis Over Canard Configuration In Turbulence Model, L V S S Lohitasya Varun, Y. D. Dwivedi

Graduate Research in Engineering and Technology (GRET)

The canard has been seen as an ominous aerodynamic object for ages this paper is to shed some more light on the effects of canard configuration on the aircraft’s wings. This flow-field analysis is thus being done using a turbulence model solution to take into the effects of a real-time environment where the vortices from the canard are captured more accurately. The analysis has been done meticulously and made to be as error-free as possible under the guidance of Dr. Yagya Dutta Dwivedi.

Effect Of Ground Proximity On Aerodynamic Characteristics Of Naca 4412 Airfoil, Aditi Deekshita Pallay, Abdul Wahab, Akhil Shesham, Y D Dwivedi

Graduate Research in Engineering and Technology (GRET)

Ground effect plays a vital role in modulating the flow behavior over any streamlined body. The most widely used wing-in ground effect (WIG) aircrafts and seaplanes utilize this phenomenon in order to enhance the aerodynamic performance during the landing and take-off phases of flight. This paper investigates the aerodynamics of ground effect on a NACA 4412 rectangular wing without end plates. The experiment was conducted in a low-speed wind tunnel at Re=2×10⁵ for the ground clearance of 1 and 0.5 of the chord, measured from the maximum thickness position on the airfoil. The pressure distribution over the chord length …

Effect Of Twin Vertical Stabilizers On Lateral Directional Static Stability Of An Aircraft – A Computational Study, K Ajay Kumar Goud, Y D Dwivedi

Graduate Research in Engineering and Technology (GRET)

The advantages of twin vertical Stabilizers over a single vertical Stabilizer of an aero plane are the rationale for this study. For conventional aero planes, the use of double vertical Stabilizers is being considered. The contribution to lateral stability has been examined for this application. XFLR5 software was used to conduct the overall analysis. The analysis was conducted for a single vertical Stabilizer as well as twin vertical Stabilizers, and the findings were compiled and correlated. It is critical to be able to fully explain and evaluate the stability and control parameters. It is crucial to understand the relationship between …

Effect Of Vertical Canard Location On Skin Friction Drag, Padakanti Saisuryateja, Y. D. Dwivedi, Raju Santhani, Abrar Md, Venkata Sai Bhanudeep Gandla

Graduate Research in Engineering and Technology (GRET)

This study investigates the viscous skin friction drag generation due to the three different vertical canard locations on the mid winger un-swept aircraft scaled-down model by using boundary layer measurements in the wind tunnel. The N22 airfoil was selected for the canard and the modified S1223 airfoil was selected for the wing. The laser cutting technique was employed for the fabrication of the wing, and canard airfoils, which gave sufficient dimensional accuracy to the model. The canard, wing, and fuselage were fabricated by balsa wood and strengthened by Aluminum stripes. The assembled model is tested in an open subsonic wind …

Design Of A Canard-Wing Uav, Venkata Sai Bhanudeep Gandla, Nirmith Kumar Mishra, Sai Kumar Algam, Vishal Yadav, Lokesh Reddy Kancharla

Graduate Research in Engineering and Technology (GRET)

In this project, we intend to design a Canard wing-based Unmanned Aerial Vehicle (UAV), which can carry a wide range of missions, providing capabilities to handle our challenges with sophisticated care. Canard-based UAV is the latest trend in aviation technology designed for the use case of providing better maneuverability, which in result gives the UAV new capabilities, such as increased time for data gathering, transferring, and autonomous behavior.

The basic disciplines like Aerodynamics, Engineering design, Flight dynamics, Propulsion, and Performance are carried out during the UAV designing process. The proposed methodology applied in this project is weight estimation, initial sizing, …

A Non-Reacting Passive Scalar Comparison Of Starccm And Openfoam In A Supersonic Cavity Flame Holder, Thomas Nuese

Electronic Theses and Dissertations

The scramjet engine equipped with a modern-day airliner would allow for very quick travel across the United States. The major problem is that designing such an engine and testing it to make sure it is safe would cost millions if not billions of dollars. Computational fluid dynamics allows for complex designs to be tested but can still take many days, weeks, or even months to complete. With the use of computational fluid dynamics (CFD), the scramjet engine can be analyzed to determine a quicker way to test and develop a reliable configuration in addition to analyzing the effects of different …

Sensitivity Of Combustion Liner Contour To Sand Ingestion Clogging, Nelson Padilla

Electronic Theses and Dissertations, 2020-

This currently presented work is an evaluation of the characteristics of different cooling hole geometries to particulate ingestion clogging. Experimentation was conducted using a premixed bluff body flame combustor facility to generate high temperature combustor flow conditions. Sand ingestion along the cooling path of the combustion liner was reproduced using an air-assisted seeder providing consistent sand ingestion. Mass flow rate of cooling air was controlled using a sonic orifice downstream of a pressure regulator so that the mass flow rate of the air and sand mixture is independent of the clogging state. Pressure data upstream of a small section of …

Aerodynamic Characterization Of An Elliptical Fairing In The Wake Of A Bluff Body, Luis Amaya

Electronic Theses and Dissertations, 2020-

Aerodynamic optimization is a key step in designing planes, cars, and even buildings. Numerical modeling is used to automate the optimization process and can use different methods to iterate through designs. In this process, consideration of the starting design is paramount as a poor choice can use up computational time and effort. Often, these designs are made with the intention of being out in the open, for which studies on shape variations in freestream situations abound. However, for the case where an object must be placed in the wake of another, there is little research. The study presented here aims …