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Aerodynamics and Fluid Mechanics Commons

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Structural Loads And Preliminary Structural Design For A World Speed Record-Breaking Turbo-Prop Racing Airplane, Matthew G. Slymen 2022 California Polytechnic State University, San Luis Obispo

Structural Loads And Preliminary Structural Design For A World Speed Record-Breaking Turbo-Prop Racing Airplane, Matthew G. Slymen

Master's Theses

The Cal Poly SLO Turbo-Prop Racer project aims to design a world speed record-breaking aircraft, capable of flying more than 550 miles per hour on a 3-kilometer closed course. To further this endeavor, this thesis presents the calculations of load distributions across the aircraft’s wing and tail and preliminary structural estimates of primary structural components for verification of the loads calculations and for use in a future finite element model. The aircraft’s fundamental design characteristics effect on the structure of the aircraft, namely the unique Y-tail design, are first examined. Then, loads are calculated in accordance with the regulation dictated …


Aerodynamic Analysis Of Morphing Wing, alugu ganesh, Anand Paul, Akshaya Reddy 2022 Institute of aeronautical engineering

Aerodynamic Analysis Of Morphing Wing, Alugu Ganesh, Anand Paul, Akshaya Reddy

Graduate Research in Engineering and Technology (GRET)

This thesis presents a modelling and design exploration study of a novel twisting wing whose motion is enabled by a tensegrity mechanism. First, the aerodynamic characteristics of the twisting wing, which does not require control surfaces to modulate its shape, are compared with those of a conventional wing having a control surface. It is shown via computational fluid dynamics analyses that the twisting wing displays higher lift-to-drag ratio than the conventional wing and hence the twisting wing is more aerodynamically efficient. In addition, due to the reduction of discontinuous rudder surfaces, morphing wings can further improve the stealth performance. A …


Aerodynamics Of Cricket Ball, shiva Shanker, ramagiri sai vamshidher, potlapalli sandeep 2022 institute of aeronautical engineering

Aerodynamics Of Cricket Ball, Shiva Shanker, Ramagiri Sai Vamshidher, Potlapalli Sandeep

Graduate Research in Engineering and Technology (GRET)

This paper describes experiments performed on stationary cricket ball to determine the aerodynamic forces acting on the ball over a range of bowling speeds. Co-efficient of drag was measured directly and it was found for the stationary ball. At air velocities above 112kmph, the drag coefficient increased with increasing air speed being weakly influenced by the vertical seam angle. Roughening one side of the ball increased the side force but delayed until a marginally higher velocity was reached. When bowler was applied to the smooth ball, the side force increased almost linearly but there was no resultant lift force. The …


Effect Of Variable Cant Angle On Sweepback Wing, Laxmi Swargam, Kidron M, Madhavi Latha Nandigam, Y D Dwivedi 2022 Institute of Aeronautical Engineering

Effect Of Variable Cant Angle On Sweepback Wing, Laxmi Swargam, Kidron M, Madhavi Latha Nandigam, Y D Dwivedi

Graduate Research in Engineering and Technology (GRET)

Winglets are commonly used drag-reduction and fuel-saving technologies in today’s aviation. The primary purpose of the winglets is to reduce the lift-induced drag, therefore improving fuel efficiency and aircraft performance. Traditional winglets are designed as fixed devices attached at the tips of the wings. However, because they are fixed surfaces, they give their best lift-induced drag reduction at a single design point. In this work, we propose the use of variable cant angle winglets which could potentially allow aircraft to get the best all-around performance (in terms of lift-induced drag reduction), at different angle-of-attack values.

This paper describes a XFLR …


A Review On Base Drag Reduction Methods, Kishore Kumar S Mr., Srinivas Pendyala Dr., Y D Dwivedi Mr 2022 Gitam University

A Review On Base Drag Reduction Methods, Kishore Kumar S Mr., Srinivas Pendyala Dr., Y D Dwivedi Mr

Graduate Research in Engineering and Technology (GRET)

In this project-based learning we are going to know about how the base drag are acting on an object to automobile and aircrafts and it deals with the equations of the drag in fluid dynamics and aerodynamics, and we come to know that what steps are we going to follow how to overcome the drag in vehicles. Reducing base drag of two dimensional and axisymmetric bodies having a blunt base. These methods include splitter plates, both thin and thick, splitter wedges, base bleed. boat-tailing and various types of serrated trailing edges. These methods include splitter plates, both thin and thick, …


Optical Microresonator-Based Flow-Speed Sensor, Elie Ramon Salameh 2022 Southern Methodist University

Optical Microresonator-Based Flow-Speed Sensor, Elie Ramon Salameh

Mechanical Engineering Research Theses and Dissertations

Optical sensors have become more prominent in atmospheric measurement systems, with LiDAR instruments deployed on a variety of earth-bound, air-borne, and space-based platforms. In recent years, the interest in the human exploration of Mars has created a substantial push towards reliable and compact sensing elements for Mars exploration missions, particularly during a spacecraft’s entry, descent, and landing stages. Real-time sensors able to reliably measure the craft’s speed relative to the surrounding atmosphere during these stages are thus of great interest. In this dissertation, a proof-of-concept for an optical microfabricated sensor, which leverages the whispering-gallery-mode (WGM) and Doppler shift principles, is …


Direct Simulation And Reduced-Order Modeling Of Premixed Flame Response To Acoustic Modulation, Zheng Qiao 2022 Mississippi State University

Direct Simulation And Reduced-Order Modeling Of Premixed Flame Response To Acoustic Modulation, Zheng Qiao

Theses and Dissertations

This dissertation introduces a general, predictive and cost-efficient reduced-order modeling (ROM) technique for characterization of flame response under acoustic modulation. The model is built upon the kinematic flame model–G-equation to describe the flame topology and dynamics, and the novelties of the ROM lie in i) a procedure to create the compatible base flow that can reproduce the correct flame geometry and ii) the use of a physically-consistent acoustic modulation field for the characterization of flame response. This ROM addresses the significant limitations of the classical kinematic model, which is only applicable to simple flame configurations and relies on ad-hoc models …


Application Of The Formal Design Of Experiments To Deformed Airfoil Testing, Alex Ligman 2022 University of Mississippi

Application Of The Formal Design Of Experiments To Deformed Airfoil Testing, Alex Ligman

Honors Theses

Traditionally, one factor at a time (OFAT) testing is used to accomplish wind tunnel
experimentation. OFAT testing is a process whereby one of the defined factors in the experiment is changed while all of the other factors are held constant. Afterwards, a new factor is chosen as the one to be manipulated, and the process is then repeated until all factors have been run through. Due to the possible cost-intensive and time-consuming nature of wind tunnel testing, formal design of experiments (DOE) has begun to be applied to wind tunnel experiments. In doing so, unique analyses can be made that …


Development And Testing Of A 1:70 Scale Model Wind Turbine Of The Iea Reference 15 Mw Floating Offshore System, Amber Parker 2022 University of Maine

Development And Testing Of A 1:70 Scale Model Wind Turbine Of The Iea Reference 15 Mw Floating Offshore System, Amber Parker

Electronic Theses and Dissertations

This thesis presents the development of a 1/70th scale performance-matched wind turbine intended for wind and wave basin model testing of commercially viable floating wind turbine structures based off of the International Energy Agency (IEA) Wind 15 MW design. The focus of this demonstration is to test active blade pitch response controls and to provide an experimental dataset for use by modelers and industry for future turbine improvements. Future research is planned to test the turbine in conjunction with an actively damping hull to test the interactions between the two control systems.

Outlined in this thesis are the methods of …


Experimental Investigation Of Supersonic Jets Using Optical Diagnostics, Theron James Price 2022 University of Tennessee, Knoxville

Experimental Investigation Of Supersonic Jets Using Optical Diagnostics, Theron James Price

Doctoral Dissertations

The complexity of many fluid flows and phenomena is a well-known characteristic driven primarily by turbulence, which has been a focal point of study for decades. Most engineering applications in fluids will encounter turbulence, and hence the need to understand how turbulence might influence the problem at hand is omnipresent. In many turbulent flows, there are large-scale coherent structures which directly influence macro-scale processes of engineering relevance, such as noise production. Over decades of study, it has been demonstrated that similar structures are often observed across many flowfields, despite differences in characteristic parameters, and this has led to the pursuit …


A Study Of Asymmetric Supersonic Wind Tunnel Nozzle Design, Brittany A. Davis 2022 Old Dominion University

A Study Of Asymmetric Supersonic Wind Tunnel Nozzle Design, Brittany A. Davis

Mechanical & Aerospace Engineering Theses & Dissertations

Achieving higher Mach numbers for private and commercial flight is a growing interest in the aerospace community. To qualify vehicles prior to flight, tests must be run in wind tunnels. Asymmetric wind tunnel nozzles are of continuing interest to the aerospace community due to their ability to change throat geometry, allowing for a range of Mach numbers to be achieved that encompasses all of the supersonic regime. The sliding block wind tunnel at Old Dominion University (ODU) is designed for a range of Mach numbers from about 1.8 to 3.5 but is limited to an upper limit of 2.8 by …


Development Of A Bio-Inspired Artificial Butterfly Vehicle, Thomas Payne Clark 2022 University of Alabama in Huntsville

Development Of A Bio-Inspired Artificial Butterfly Vehicle, Thomas Payne Clark

Honors Capstone Projects and Theses

No abstract provided.


Computational Analysis Of The Effects Of Scarfed Nozzle Variations On Jet Plumes, Andrew J. La Sorsa 2022 Ohio Northern University

Computational Analysis Of The Effects Of Scarfed Nozzle Variations On Jet Plumes, Andrew J. La Sorsa

ONU Student Research Colloquium

A computational fluid dynamics analysis investigating the variation of effects on nozzles with non-orthogonal exit planes, known as scarfing, was performed. The steady Reynolds-averaged Navier-Stokes model, coupled with the Spalart-Allmaras turbulence model, was used to simulate and compare plume development and characteristics using various scarfing geometries at variable inlet conditions. The jet plume cross-section is significantly affected for overexpanded conditions, while retaining the nozzle exit shape for underexpanded conditions, although slight peaks (bifurcation) do occur at the centerline. The same observations occur when slightly changing the angle of scarf. However, inverting the overall geometry of the diverging portion of the …


Effects Of Vortex Generator Placement On A Horizontal Axis Wind Turbine Blade, Dagan Sorensen 2022 Ohio Northern University

Effects Of Vortex Generator Placement On A Horizontal Axis Wind Turbine Blade, Dagan Sorensen

ONU Student Research Colloquium

Vortex generators are commonly used devices to control the flow over an airfoil or other surface. In this paper the effect of differing placements of vortex generators on a wind turbine airfoil, compared to an airfoil without vortex generators, were simulated using computational fluid dynamics(CFD). It was shown that, in some instances, the application of vortex generators effectively controlled the flow over the airfoil to increase the power produced by the wind turbine. According to the CFD results, the application of vortex generators at an angle increased the lift produced, as well as delaying the separation of the boundary layer.


Effect Of Anhedral And Dihedral On The Lateral Directional Static Stability Of The Aircraft, Girish Kumar Chowdary Kanneganti, Bhaskar Charan, Vesapogu Chandrakala, V. Varun Dr. 2022 INSTITUTE OOF AERONAUTICAL ENGINEERING

Effect Of Anhedral And Dihedral On The Lateral Directional Static Stability Of The Aircraft, Girish Kumar Chowdary Kanneganti, Bhaskar Charan, Vesapogu Chandrakala, V. Varun Dr.

Graduate Research in Engineering and Technology (GRET)

Developments and advancements in Aircraft industry have led to an increasing the stability and maneuverability of an aircraft. When the aircraft subjected to unbalanced force it needs the suitable wing to overcome the side slip and maneuverability of an aircraft. This work proposed a Dihedral and Anhedral wing simulation in XFLR5 software to increase the stability and maneuverability of an aircraft. XFLR5 analysis was then carried out for Dihedral and anhedral angles of 5deg, 10deg ,with side slip angles 2deg and 5deg. The aerofoil used in wing is NACA 4412 and in tail is 0009..Lateral-Directional Static Stability of 5,10 deg …


Effect Of T-Tail On The Aerodynamic Characteristics And Static Stability Of An Aircraft – A Computational Analysis, Athar Mahmood Ansari Mr, Amarnath M Mr, Ambati Joseph Leonard Mr 2022 institute of aeronautical engineering

Effect Of T-Tail On The Aerodynamic Characteristics And Static Stability Of An Aircraft – A Computational Analysis, Athar Mahmood Ansari Mr, Amarnath M Mr, Ambati Joseph Leonard Mr

Graduate Research in Engineering and Technology (GRET)

It is the purpose of this paper to find out the effect of T-tail on Aerodynamic characteristics and static stability of an aircraft. A T-tail aircraft with a configuration of tail with the horizontal stabilizer placed above the vertical stabilizer. Typically, a tail configuration in T shape. T- tail configuration is proposed with a goal of enhancing stability and controllability during high angle of attack and low speeds. Data is presented from a series of XFLR5 analysis to qualify the aerodynamic effect of T-tail over a range of angle of attack from -150 to +150. Various …


Effect Of Dihedral And Anhedral On Lateral-Directional Stability Of Rectangular Swept Back Wing, Bhavya Poojari 2022 Institute of Aeronautical Engineering

Effect Of Dihedral And Anhedral On Lateral-Directional Stability Of Rectangular Swept Back Wing, Bhavya Poojari

Graduate Research in Engineering and Technology (GRET)

Abstract:

This paper investigates the probable effect a dihedral and an anhedral have on the Lateral-directional stability of an aircraft. In this paper we discuss the basic design of a rectangular swept back wing, designed in the XFLR5 software. We will apply different angles for both the dihedral and anhedral and analyse it using the XFLR5 Software. Our main goal would be to understand the stability criterion, mainly lateral-directional, of the airplane, analysing the graphs that help us understand lateral-directional static stability, compiling all the results and concluding our findings. Furthermore, we will be well-versed in the domain of static …


Aerodynamic Analysis Of Delta Wing At Low Reynolds Number Using Computational Simulations, C Manoj Kumar Reddy, DIVYASUNDER MANNE, Nisha Tirumallasetti 2022 Institute of Aeronautical Engineering

Aerodynamic Analysis Of Delta Wing At Low Reynolds Number Using Computational Simulations, C Manoj Kumar Reddy, Divyasunder Manne, Nisha Tirumallasetti

Graduate Research in Engineering and Technology (GRET)

The delta wing is best known for their contribution to stability and also, they have high structural advantages compared to other wings. Till now the delta wing has been used mostly in high speed or high Reynolds number flows. But no one concentrated on the low Reynolds number flows, here we have analyzed the flow at Re = 100000. Since we have taken the case of this Reynolds number range, the results obtained can be utilized in designing the Micro Air Vehicles (MAVs) which are mostly designed for the range of Reynolds number Re = 10000 to 100000. We have …


Xfoil Analysis On Low Reynolds Number Airfoil, Pabbu Pavithra, Emmadi Parimala 2022 Institute of Aeronautical Engineering

Xfoil Analysis On Low Reynolds Number Airfoil, Pabbu Pavithra, Emmadi Parimala

Graduate Research in Engineering and Technology (GRET)

The range of low Reynolds number airfoil is between 104 to 105.In this study the investigated airfoil is NACA2414.The aerodynamic performance of low Reynolds airfoil is less than 105 is important for various applications such as unmanned air vehicles, Micro air vehicles and low-speed/high altitude aircrafts. In general, the lift and drag characteristics of most of the airfoils cannot be assumed constant having Reynolds number less than 106. XFLR5 is an analysis tool for airfoils, wings and planes operating at low Reynolds numbers. It includes XFOIL’S direct and inverse analysis capabilities. Wing design and …


Flow Analysis On Delta Wing – A Review, Y D Dwivedi, C Navaneetha, Vasishta Bhargava 2022 Institute of Aeronautical Engineering, Hyderabad

Flow Analysis On Delta Wing – A Review, Y D Dwivedi, C Navaneetha, Vasishta Bhargava

Graduate Research in Engineering and Technology (GRET)

Many aircraft, like fighters and bombers, are delta-winged aircraft. These aircraft have the characteristics of producing a greater lift at very small angles of attack even at very low Reynold’s number. Highly swept-wing aircraft experience greater lift due to the generation of the leading-edge vortex at a high angle of attack flight. The phenomena of vortex breakdown are noticed which leads to the reduction of the vortex lift and leads to the instability of the aircraft. This paper deals with an analysis of the flow on the delta wing with the existing literature and compares its benefits over the conventional …


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