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Improved transportation increased the amount of fuel consumption required. Transportation in Indonesia is the largest oil-consuming sector, with a percentage of 40.1% of the total. Vehicle manufacturers are required to produce a vehicle that has a high level of fuel efficiency. This study aims to determine the aerodynamics of energy-efficient vehicle bodies based on computational fluid dynamics (CFD). This research was conducted using SolidWorks to implement the model. This study examined the variations in airflow velocity at 25, 40, 55, and 70 km/hour. It can be found that the coefficient of drag (Cd) values of the latest body designs with variations in airflow velocity were increased value. The calculation results of the coefficient of drag values were 0.149, 0.154, 0.162, and 0.162, respectively, and the average value was 0.156. In this research, we have found that the energy-saving car body can reduce the drag coefficient compared with the previous study. [ABSTRACT FROM AUTHOR]

The decreasing performance happens on the airfoil due to a dent on the leading edge part. This problem occurs due to a bird strike. This article investigated the characteristic aerodynamics comparisons of the original airfoil NACA 2412 and the dent airfoil NACA 2412. The applied analysis was with ANSYS Student 2022RI. The researchers compared the lift and drag coefficients for both airfoils within the striking angle between 0⁰-6⁰. The researchers kept the free-airflow constant under the same airflow conditions on the Reynold number of 3.1 x 106. The study used the k-ω SST turbulence model to accurately calculate the airfoil surface flow. According to the simulation results, the lift coefficient (CL) of dented NACA 2412 airfoil decreases while the drag coefficient (CD) increases. The value of CL and CD fluctuates with the angle of attack variations, and it is caused by disturbances in the pressure distribution. [ABSTRACT FROM AUTHOR]

Airfoils, which are basically the wings of an aeroplane, are an essential part of aerodynamics and aviation, greatly influencing the lift and drag properties of an aircraft. Aerodynamic performance can be strongly affected by flow separation, a phenomenon where the airflow over an airfoil separates from its surface. The paper uses MATLAB numerical simulations to examine the effectiveness of many flow separation control strategies. A significant challenge in aviation is flow separation, which has an impact on the lift-to-drag ratio and overall aerodynamic efficiency. Many strategies have been researched to tackle this problem, including active and passive control approaches. Leading-Edge Blowing, Boundary Layer Suction Control, and Angle of Attack Control are some of these methods. The paper's two main goals are to evaluate how different strategies affect airfoil performance and to pinpoint the most efficient way(s) to increase aerodynamic efficiency. Using a range of airfoil designs, flow conditions, and simulations at different angles of attack and Reynolds numbers, the process entails numerical research. Every control method has a mathematical model that has been carefully created and put into practice in MATLAB. The research paper's observations provide important new information on how well flow separation control strategies works. The data, graphs, and analysis that are provided show how various methods affect important aerodynamic factors including lift, drag, and pressure distribution. Even with flow separation's drawbacks, this study highlights how creative control strategies can improve airfoil performance. These results add to the growing body of knowledge in the field of aerodynamics, deepen our understanding of flow separation control, and lay the groundwork for further investigations aimed at improving aviation efficiency and safety. [ABSTRACT FROM AUTHOR]

Due to depletion in raw material quality, blast furnace (BF) aerodynamics, hence the permeability uses to be disturbed in BF#8, Bhilai Steel Plant (BSP). Deviation in middle zone permeability of BF#8 suggested the deviation in cohesive zone shape and position. For better understanding and monitoring of the lower zone permeability of BF#8, BSP, two models were developed. The models were Cohesive Zone (CZ) shape and position prediction model and online presentation of Dead-man clinginess Index (DCI). Use of CZ model is helping in assessment of type of cohesive zone shape through which burden distributions as well as blast parameters arebeing regulated. Hearth cleanliness condition is monitored through online DCI model. Use of DCI is helping in devising the optimum casting strategy for proper drainage of liquid products and also to maintain healthy and active hearth. [ABSTRACT FROM AUTHOR]

This work aims to present an alternative time domain modeling approach for preliminary flutter analysis of wings equipped with trailing edge control surfaces. The proposed modeling approach is based on the formulation of an aeroelastic beam finite element that relies on Euler-Bernoulli beam theory and De Saint Venant torsion theory for the structural part and on Theodorsen theory for aerodynamics. The modeling approach here presented is useful for preliminary aeroelastic analysis and it could be readily implemented in existing beam finite elements-based codes. [ABSTRACT FROM AUTHOR]

Mitigation of total pressure loss and improvement in aerodynamic performance are obtained on a low aspect ratio turbine blade. The turbine blade hub region is constructed with a boundary layer fence to reduce secondary losses. The major objective of implementing boundary layer fence is to restrict the pressure side leg of horseshoe vortex from reaching suction surface of adjacent blade. This decreases the loss associated with the passage vortex by delaying its development. Present analysis reveals the aerodynamic performance of boundary layer fence in three ways. Firstly a rectangular strip is kept close to the suction surface in order to break the suction side leg of horseshoe vortex. Secondly, to restrict the pressure side leg of horseshoe vortex from traversing from pressure surface to suction surface a fence of curved trailing edge is kept at the middle of the blade passage. In the third configuration the combined effects of both rectangular strip and fence have been analyzed. In this work the shape of the rectangular strip and fence do not follow the blade profile. Ansys-cfx, commercial software is used for numerical analysis. The results indicate that the presence of strip has resulted in the breakdown of suction side leg of horseshoe vortex and the location of fence has directed the pressure side leg of horseshoe vortex more axially rather than traversing across the blade passage. The combination of both geometries has achieved further reduction of total pressure loss coefficient. [ABSTRACT FROM AUTHOR]

Accurately predicting the motion of resident space objects requires knowledge of all forces acting on these objects. Ionospheric aerodynamic forces, resulting from the interaction of charged bodies with the plasma medium, have been shown to constitute a significant increase in aerodynamic drag in many regimes of low earth orbit (LEO). Previous work on charged aerodynamics has considered only single species plasma flows, neglecting the multi-species interactions in the region of the ionosphere where O+ and H+ mix. We focus on H+ dominated higher altitude regime. The simulations are performed using a hybrid electrostatic particle in cell code (pdFoam). Distinct drag characteristics of H+ and O+ were identified, and related to the sheath structure for each of these regimes. Drag coefficients for high charge density flows with a mix of H+ and O+ were found to behave in a manner similar to a pure H+ flow, with the O+ component behaving similarly to a neutral flow. This results in a reduction in drag contributed by the Oxygen plasma in these mixed flows. Drag forces on these flows were found to be well predicted by the use of the drag prediction model in Capon et al [1] for H+ components, and equivalent neutral oxygen density for oxygen components. [ABSTRACT FROM AUTHOR]

A series of wind tunnel testing of a medium altitude long endurance (MALE) unmanned aerial vehicle (UAV) have been carried out resulting in a set of aerodynamic data. In the current study, the data are used to determine the effect of the tail and the ruddervators that are attached to it. In general, the tail enhances aerodynamic forces especially due to the sideslip angle and also provides the components of stability both in the longitudinal and lateral-directional motion. The ruddervators also alter the aerodynamics and the stability even though there are slight differences between the right and the left ruddervator hence asymmetric flight is expected. At high sideslip angles, peculiarities start to occur giving, most noticeable in drag production and lateral motion. The findings in the study are essential to obtain further information on the dynamic stability analysis and flight characteristics of the UAV. [ABSTRACT FROM AUTHOR]

Aerodynamics are fundamental to the daily lives of us living primarily in a gaseous environment we call air. It can be observed in many daily things such as piping, vehicles, and buildings. Aerodynamics can play a crucial part in safety or efficiency of an object. Design engineers must include aerodynamic calculation into consideration, especially if it includes safety, such as buildings, bridges, and other important structures. Cylinder is one of many geometries profile that can represent specific flows which occurs on such applications. Design engineers now have the option of using a CFD software to aid them through the process of engineering. This software takes almost all parameters into account and calculate them according to the user choice of subject. This research is aimed to investigate the flow around cylinder model using CFD method of AF1300a. The simulation is done using ANSYS CFD software, at 5 different speeds (1,39 m/s, 2,78 m/s, 4,17 m/s, 5,56 m/s, and 12,5 m/s) with 3 different mesh smoothing options (low, medium, and high smoothing) which results in different number of nodes and elements of the mesh. The result shows medium and high smoothing mesh to have similar output in pressure area, and velocity area. So medium mesh smoothing is enough for the next research as the optimal mesh smoothing option. The results of this research will be used for future research on vehicles aerodynamics. [ABSTRACT FROM AUTHOR]

The ability to study a flow field to improve efficiency or performance is one of the leading areas of research for many scientists and engineers in fluid mechanics. Through CFD simulations around a 2D sport utility vehicle model, this research highlights the impact of the airflow around the side contour of the vehicle. Attention is given only to the external design of the car, while the interior is not modeled. The goal is to simulate the air flow around the vehicle and obtain an accurate value of its drag and lift coefficient. The next step would be to make modifications to the vehicle geometry which could improve its lift and drag characteristics making the vehicle handle better at cruise speeds and also improve its fuel efficiency. [ABSTRACT FROM AUTHOR]

This article describes the process of the air flow in the double skin transparent facade (DSF) during the summer period in the windless condition by natural convection and mechanical airflow by means of heat recovery unit during the winter period for reducing energy needs of the building during the winter and summer period. Utilizing a renewable source of solar energy by transforming short-wave solar radiation into long-wave heat radiation in physical cavity of the double skin transparent facade with a positive reduction of energy flows to the building core (reduction of heat load from solar radiation during the summer period and elimination of the heat losses during the winter period), by using temperature-treated air from the cavity of the double skin transparent facade in winter period for the facade heat recovery unit integrated in the facade element with positive impact on reducing the energy demand for heating. With the correct geometry or the regime of the double skin transparent facade, we can reduce overheating in the summer and we can use the heat-treated air from the cavity effectively in the winter. [ABSTRACT FROM AUTHOR]

Winglet considers one of the most effective ways to reduce wingtip vortices, and since winglet is discovered, much research has been made to improve its work. Different parameters can be enhanced to optimize the winglet work. So, in this paper, the aerodynamics characteristics of the winglets analyzing at different cant angles and span of winglet values to improve the winglet performance. Four different cant angles were studies, and three different winglet spans of a semi-span wing were considered. All the models were tested for four Angle of attack values. Then, the values of lift to drag ratio calculated to choose the model with highest lift force and the lowest value of drag. All wing models (fifty-two models) are modeled in 3D using SOLIDWORKS software based on wing dimensions of 737-800 Boeing, then the models are analyzed utilizing ANSYS FLUENT. The calculation shows the values of the cant angle and span of winglet influence on the performance aerodynamic of aircraft versus AOA. The best ratio of lift to drag value was found in model with a cant angle 60o, winglet span 20%, and AOA 5o. [ABSTRACT FROM AUTHOR]

In this study, the turbulent flow over symmetrical and unsymmetrical airfoils was investigated numerically at different inlet velocities. The airfoils chosen for the simulation are symmetrical (NACA 0015) and unsymmetrical (NACA 4412), which are the most conventional four-digit and widely used airfoils. These airfoils are vastly used for various applications such as aircraft wings, wind turbine blades, etc. While both of these airfoils were subjected to the same fluid principle, it gave contradictory results in their aerodynamic behavior. In this paper, two different meshing techniques were used for the airfoils and the numerical analysis of NACA 0015 and NACA 4412 was carried out to study their aerodynamic behavior. A 2D steady-state incompressible turbulent flow is used to model the computational issue. The performance of the turbulence model is also reviewed. The lift and drag coefficients of the airfoils were numerically measured using the k − ε turbulence model. This study briefs the aerodynamic flow characteristics of both airfoils and evaluates the pressure and velocity contours, lift force and drag force. [ABSTRACT FROM AUTHOR]

The winglet is one of the best ways to reduce fuel consumption due to minimizing the drag generated at the wingtip. This study aims to determine the optimal winglet orientation and the influence of winglet Toe and Twist angle combination upon the aerodynamics performances of an airplane wing for Boeing 737 wings at Mach 0.78 in terms of lift-to-drag ratio. First, a sixty winglet models were drawn using SOLIDWORKS software, with various Toe angles (+10°, +5°, 0°, -5°, and -10°) and Twisted angles (-5°, 0°, and +5°) at (4) attack angles (0°, 3°, 6°, and 9°), with assumptions of the winglet Cant angle of 60°. A winglet span of 3.5 m was examined. Second, using analysis of systems Fluent, a computational fluid dynamics analysis of the wing-winglet arrangement based on the Boeing 737 airfoil on drag reduction at different attack angles was done. This analysis indicated that modifying the arrangement of the winglet's Toe and Twist angles can increase the aerodynamic performance at various attack angles. The lift to drag ratio value was calculated to decide which wing possesses the best aerodynamic characteristics. The best value of lift to drag ratio is equal to 18.67 at twist angle +5°, toe angle -5°, and AOA 3°. The lowest value of lift to drag ratio is equal to 5.23 at twist angle 0°, toe angle -10°, and AOA 0o, the percentage difference between the two model values equal 113%. [ABSTRACT FROM AUTHOR]

The imperative job of the wing in lift age is reliant with wing boundaries. It has been seen that there have been changes in the wing setup throughout the long term and more often than not is spent on improvement. In this exploration, we expect to approve and improve the wing effectiveness utilizing various methodologies specifically computational, mathematical and test on various kinds of wings. Computational investigation is performed utilizing ANSYS Fluent Software, the mathematical examination is accomplished utilizing diverse addressing techniques and the exploratory examination is done utilizing wing setup testing. The outcome acquired in this examination project yield plots and qualities for CL and CD with various stream shapes. Eventually, the report made would furnish us with a superior viewpoint on the extent of advancement in different regions. Three diverse wing plans with a similar airfoil, range, and mean streamlined harmony are investigated. Different Aerodynamics attributes like lift and drag are to be inspected and thought about for these three unique wings. The three wings are rectangular, tightened, and cleared made in CATIA V5 and its investigation is done in Ansys Fluent. [ABSTRACT FROM AUTHOR]

The possibility of decreasing the drag coefficient of the slotted airfoil is investigated at Reynold number 1.6 x106 for the angles of attack were ranged from 0°to 20°. For this purpose, the edges of the simple slot airfoil had been made with curve edges. The numerical study was evaluated by using ANSYS fluent 21.0 with κ-ω SST turbulence to solve the fully turbulent Navier-stocks equations. The location and dimensions of slot had been adopted from the previous consideration where fixed at exit slot at 60% chord, the orientation by 65° and 1%chord width of slot. The edges were rounded to make the flow streamed with the airfoil surface. The results showed that this method has decreased the drag coefficient at entire range of angles of attack with increasing in lift coefficient at angels ≥14° and delaying stall angle from 15° to 19°. The maximum increasing in lift to drag ratio was 3.9 times the ratio for solid airfoil at angle of attack 17°. [ABSTRACT FROM AUTHOR]

Aerodynamic drawbacks of intercity bus profile have become a concern since it generates a considerable large value of drag coefficient. The study aims to propose some options to improve the aerodynamic profile of the external body shape of a bus to produce a better aerodynamic performance. The adopted aerodynamic profile improvement from current aerodynamic devices from other types of vehicles has chosen to modify the external shape of a bus. The study presents the numerical value of the resulting drag coefficient and lift coefficient for each proposed bus profile modification. It compares the resulting value from the original bus model to other modified models The visual comparison of the resulting pressure coefficient around the bus, velocity contours, and resulting turbulence kinetic energy assists the readers to better understand the aerodynamic behavior of the modified bus profile. The overall comparison indicates that combining all proposed additional aerodynamic devices and reshaping the bus profile largely benefits in the drag reduction compared to the original bus model, which leads to 0.09 point of drag reduction. Each modified part positively contributes to better airflow around the bus model. [ABSTRACT FROM AUTHOR]

Each year, India sells a large number of tiny engines (two-wheelers). Its emissions account for a large proportion of India's total pollution. Improved fuel mixture control and fewer emissions from small engines could result from a better understanding of Turbo charger nozzle performance and modeling. A commercial computational fluid dynamics package might be used to generate a three-dimensional, totally turbulent model of compressible flow across a complex geometry venturi, such those found in tiny engine Turbo charger nozzles. The results of the CFD simulation might be used to figure out how different flow obstacles affect the mass flow rate and static pressure at the fuel tube's tip. This could be helpful in determining the amount of pressure lost in the neck. An examination of airflow over theturbo charger nozzle venturi would be performed by putting the fuel tube at the venturi's diverging nozzle and for various throttle valve locations. At various throttle opening stages, the performance of the turbocharger nozzle would also be investigated. The turbo charger nozzle body would be rebuilt in the second phase of the project, with two throttle bodies replacing the standard throttle. A flow field analysis with a changed design would be carried out. In addition, a thorough comparison of the existing and updated designs would be carried out. [ABSTRACT FROM AUTHOR]

A mathematical model of the movement of solid particles in an ascending stream of an intensified fluidized bed is shown. Mathematical formulas defined describing the trajectories of the diets of solid particles depending on the speed of the gas flow. The results of theoretical calculation are compared with the physical experiment data. A comparative analysis shows the adequacy of the results obtained. Study and the possibility of using them in solving engineering problems on thermal processing of dispersed and polydisperse materials in intensivied fluidized bed. [ABSTRACT FROM AUTHOR]

The deployment of aerodynamic kits in formula one cars significantly shown the performance of the cars in various aspects. This makes us to work and improve the aerodynamics of a formula student car. This report clearly outlines the design and optimization of undertray diffuser for formula student car. Formula one car reaches maximum top speed of 370 km/hr. but a formula student car reaches only a top speed of 120 km/hr. Due to the high speed of the formula one car, all aerodynamic kits such as front splitter, rear wing, diffuser are employed and work efficiently at that highspeed. Due to the low top speed of formula student car, the rear wing and other kits does not work efficiently. Among those kits, the undertray diffuser tends to work efficiently for a formula student car owing to its low top speed. So, for a formula student car, it is better to work on undertray diffuser. The diffuser acts as an expansion chamber to manage the air which exists underneath the car. It increases the pressure of low-pressure and fast-moving airstream back to the ambient atmospheric pressure at the exit of diffuser. Smoothing this transition reduces turbulence and drag in the car. [ABSTRACT FROM AUTHOR]

Even though symmetrical airfoil has less lift-drag ratio and the undesirable stall characteristics it has been used in the rotary wing applications. Increasing the aerodynamics efficiency by using the different flow control methods are the important research in recent years. Amplifying the lift coefficient without causing any negative impact on the drag coefficient will create the great impact on aeronautical domain. Hence this paper objective is by using cylinder rotation- an active flow control method to improve the aerodynamic efficiency over the airfoil. To get the optimum values of lift and drag coefficient the flow parameters, velocity ratios of the cylinder Vc / V∞ and the location of the cylinder have been used. The model of the NACA 0012 airfoil with cylinder is developed by using Inventor and the numerical analysis were carried out by using Ansys fluent. Analysis was carried out for the velocity ratios of 0.5,1 and 2 by placing the cylinder at the chordwise locations of 10% to 50% of its length. When compared the results of NACA 0012 airfoil with cylinder and without cylinder there is a significant growth in aerodynamic efficiency and delayed in stall angle. Generally, the performance was increase in the ratio of cylinder rotation speed Vc to the freestream speed V∞. There appears to be an optimal location for the rotating cylinder which gave quite promising results. [ABSTRACT FROM AUTHOR]

The use of fossil energy is very influential on environmental sustainability. The impact we have felt is global warming with an uncertain season. So we must have a commitment to reduce the consumption of fossil fuels in order to maintain a sustainable environment. This is in line with the commitment of the University of Lampung (UNILA) in making the Unila campus a Green Campus. One of the technologies that can encourage the realization of a green campus is electric vehicles around campus. The purpose of this analysis is to determine the design of the shape or geometry of the vehicle and the aerodynamic analysis of the vehicle with speed variations of 10 and 20 m/s. This research uses the Research and Development (R&D) type of research and is carried out to make an optimal vehicle design with aerodynamic studies. This study uses the Software Ansys Workbench with CFD solver and using m etode k-epsilon turbulence realizable standard wall function. [ABSTRACT FROM AUTHOR]

Energy is the source of human life to be able to carry out its activities. The more energy that is used, the more the impact that will be caused especially the energy used is non-renewable energy. So for sustainability, the development of energy sourced from renewable energy is carried out. One of them is Electrical Energy. Utilization of wind energy into electrical energy can be produced with a conversion tool, namely a wind turbine. This study aims to design and analyze the fluid flow that occurs in the wind turbine according to the design. The research will be carried out design using the wind turbine using Q-blade software. This research uses the NACA airfoil 4412. At this stage of the simulation, there will be a wide range of variation of the wind velocity that is 1 to 7 m/s, Tip Speed Ratio (TSR) and variation of pitch angle in order to generate maximum value. In the design this study, the maximum wind turbine design was obtained. [ABSTRACT FROM AUTHOR]

In the design of hypersonic and supersonic vehicles, the critical challenge will be the phenomenon of shock wave interactions. It becomes increasingly important because the aerodynamic heating and pressure loads raises so greatly that the performance of the flight and the basic structure are going to be largely affected. In the present paper we performed a numerical model of the problem and analyzed using a commercial Computational Fluid dynamics software, and compared the results with the published data. The key element that we have considered is the double wedge problem and studied the characteristics of the aerodynamics using CFD. The conditions of type III and IV interactions are studied. Our analysis successfully characterized the shock wave interactions. Almost very similar conclusions were made by the published results. There has been a zone of the shockwave interaction and the intersection of this zone has been shared with the intersection of second shockwave due to the second wedge. The slip lines are not observed as the inconsistency. [ABSTRACT FROM AUTHOR]

The purpose of this paper is to study the influence of vortex flow aerodynamics in the inter-pipe space on the pressure loss in the classifier with coaxially arranged pipes. The results of studies showed that the developed design of classifier with coaxially arranged pipes allows to create a stable vortex structure in the inter-pipe space. In this case, the pressure loss in the classifier is not more than 1000 Pa while the inlet gas flow rate is within the range of 7.3–22.2 m/s. The minimum pressure loss in the classifier, not exceeding 805 Pa, was obtained for all open round holes in the inner cylindrical pipe. In the course of physical experiments, power dependences were obtained. The degree of obtained functions, characterizing the dependency of pressure loss in the classifier on the inlet rate, varies from 1.64 to 1.68. The discrepancy between the physical experiment and the numerical simulation is within the range from 2.2 to 22.5% when the inlet gas rate varies within the range from 8.94 to 22.2 m/s, which, on the one hand, requires additional study, on the other hand, shows that the numerical simulation at the specified parameters can be used for estimation calculations. [ABSTRACT FROM AUTHOR]

The major challenge in aerodynamics is the reduction of drag for high-speed vehicles. Re-entry vehicles usually travel at hypersonic speeds, because of this, they experience high temperature and drag force. One of the ways to reduce the heating and coefficient of drag is by using spike. In the present study we have numerically investigated the aerodynamic performances of a blunt body with sharp spike and hemispherical spike with different length to base diameter ratio using ANSYS fluent. We have compared the performance of the bunt body with and without spike. Density based solver and explicit method have been used as it is most preferred for high-speed flows. Simulations have been carried out at three different Mach numbers 4, 5 and 6. Effect of semi vertex angle of the sharp spike is also studied. Results are validated with the available literature. It is observed that drag coefficient increases with increase in Mach number, semi vertex angle and decreases with increase in L/D ratio. It was also found that both drag coefficient and Heat flux were minimum for hemispherical spike when compared to others. [ABSTRACT FROM AUTHOR]

A simulation of the aerodynamic features of the vehicle has been carried out. The analysis was carried out to determine the impact of various design features on the drag force and lift force acting on the vehicle. A scaled prototype of a hatchback car (Skoda FABIA) was used as a base model. The geometric model of the hatchback car was created in Onshape, an online product development platform using a surface modeling technique. The selected design features of the car were modified to improve the drag and increase downforcewhich acts on the vehicle. Asimulation for vehicle aerodynamics was performed in AnsysFluentsoftware to compare the drag,liftcoefficientinthe case of the base model and the modified model. The simulation results indicate that adding roof contours to the model and changing some turbulence reducing shapes such as dimensions alongwiththewindshield, front, and rear bumper heightnotablyreduced the amount of drag acting on the vehicle. [ABSTRACT FROM AUTHOR]

The article examines the issues of aeration modelling (organized natural air exchange) in quarries using guiding devices. The simulation was carried out in a wind tunnel, which makes it possible to study the aerodynamics of air currents in the goaf and evaluate the effectiveness of the use of the guiding device. The design of a closed-circuit wind tunnel and the modelling technique are considered. [ABSTRACT FROM AUTHOR]

Dual system hybrid VTOL UAV is one type of UAV that can take-off and landing using their rotary-wing system and cruise with their fixed-wing system. In this type of UAV, there is two propulsion system, the first one is a propulsion system for vertical take-off and landing and the other is for forward flight. This type of UAV is selected because of their easiness of transition between rotary and fixed-wing mode. This paper provides the dual-system hybrid VTOL UAV preliminary design without horizontal tail configuration. The objective of the UAV is to deliver three blood bags or another payload with a mass of 1.5 kg within the 100 km range. This paper also provides the aerodynamics and energy usage analysis of the designed UAV. The aerodynamic analysis is conducted using XFLR5 v6.47 and ANSYS Fluent 2019 R3. [ABSTRACT FROM AUTHOR]

The LSU-05 NG (LAPAN Surveillance UAV-05 New Generation) is the new generation of LSU-05 unmanned aircraft designed by the Aeronautics Technology Center of LAPAN. This aircraft uses a U-tail configuration that is connected with two booms, but the boom on the LSU-05 still has problems with its deflection that is too large, thus disrupting the aerodynamics of the aircraft. This report contains an analysis of the tail boom structure of the LSU-05 NG. ABAQUS/CAE software is used to predict the deformations that occur in structures. This analysis offered 3 configurations with different boom cross-sections that are subject to gravity. The results of the analysis show a comparison of the three boom configurations offered and also have the conclusion that the entire empennage structure is still safe. [ABSTRACT FROM AUTHOR]

Investigation of supersonic flows in internal channels of various geometries is widely problem of aerospace. Nowadays, the ramjet engine with supersonic combustion is an advance engine for hypersonic aircrafts and space vehicles. The study of operating principle and mechanics of ramjet can be simplify to study of supersonic flow in a profiled internal duct simulates a section of a working path or fuel chamber. The aim of study is an experimental and computational study of supersonic flow in an internal axisymmetric internal channel with sudden expansion at case of oncoming flow velocity of M = 5 and M = 6. The proposed devices for pressure and temperature on wall of duct recording are described. The comparison of results of measurements in aerodynamic tests and corresponding numerical calculation is presented. Close agreement for experimental and numerical calculation obtained. Based on correlation of aerodynamic tests and simulation results verification of previously proposed approach for solve problem of flow around model in test section of aerodynamic wind tunnel presented. [ABSTRACT FROM AUTHOR]

Aerodynamic wind tunnels the one of the widely used tools for aerophysics research. The wind-tunnel test technique allows the results of experiments transferred on full-scale objects. In view of the complexity of recording in supersonic flows, the numerical simulation affords opportunity to make more full description of process and to obtain distribution of gas-dynamic parameters. The purpose of the research is mathematical simulation of gas movement in internal volume of an impulse aerodynamic wind tunnel. For mathematical description of process Unsteady Reynolds averaged Navier-Stokes equations are used. The initial and boundary conditions are chosen according to aerodynamic experiments. By the numerical calculation a gas-dynamic parameters in steady supersonic flow on the edge of axisymmetric nozzle are obtained. Results of simulation corresponds with quasisteady flow regime in real aerodynamic tests. Obtained data can be used to solve a wide range of problems, theoretical and engineering analysis of experimental results. [ABSTRACT FROM AUTHOR]

We report on the aerodynamics and scalar characteristics of a premixed swirl-stabilized propane-butane/air flame at the exit of a radial vane swirler. The experimental study focuses on the combustion of a well-premixed lean fuel/air mixture Φ = 0.57 with varying guide vane angle and hence with varying swirl number S. Mean velocity profiles are measured using laser Doppler anemometry, and mean temperature distributions are obtained by thermocouples. Optimal operating regimes of swirl- stabilized combustion are determined from visualization data, temperature distributions, and velocity profiles for different values of the geometric swirl number S. For the reacting and isothermal cases, the precessing vortex core is identified by power spectral density analysis of fluctuations of the tangential velocity at the center point of the central recirculation zone. It is shown that the precessing vortex core is determined by well-mixed isothermal swirl flow in the mixing tube of the radial vane swirler. [ABSTRACT FROM AUTHOR]

The conceptual design of the hydrogen-fueled detonation ramjet (DR) of a new type for a cruising flight speed of Mach 2 at sea level is developed using 3D numerical simulations of the operation process. The calculated effective thrust of such a DR is shown to become positive at M = 1.3, i.e., the startup Mach number for such a DR can be lower than M ≈ 2.0, which is typical for ramjets operating on continuous-deflagration combustion. A DR demonstrator is designed and manufactured. Its test fires are performed in a blowdown wind tunnel (WT) at free air jet Mach numbers M = 2.0, 1.5, and 0.9. The result of test fires is the experimental proof of the possibility of arranging stable continuous-detonation combustion of hydrogen in the DR of the developed design at both Mach numbers exceeding 1.0. The maximum measured values of the fuel-based specific impulse and total thrust were 1610 s and 650 N for the tests with M = 1.5 and 1630 s and 860 N for the tests with M = 2.0. [ABSTRACT FROM AUTHOR]

Diffuser is the important feature of turbo-machinery, which is used for the efficient conversion of kinetic energy into pressure energy. The diffusers need to be specially designed due to space constraints in aircraft applications so that one can achieve maximum pressure recovery within the shortest possible length and this challenge led to the optimization of annular diffusers. In the present study, the aerodynamic performance analysis of annular diffusers of various geometry and the geometric optimization of the annular diffuser has been performed for the given set of geometric constraints. For the evaluation of flow development in the annular passage geometric parameters are varied and their effect on the capacity of the diffuser. A response surface optimization technique is performed on the annular diffuser geometrical parameters using ANSYS Design Xplorer and six different best performed design solutions/candidate were obtained. Among six geometry, two best performing geometry set has been selected as best candidate. The different response surface, sensitivity analysis conveys some important outcomes, for the optimization are: The parametric sensitivity leads to the picture of the three design variables have a significant impact on performance and plays a vital role to understand the flow behavior. The hub angle and the length have the dominating effect on pressure recovery capacity with that of shroud angle. The performance improvement was accompanied by change in the geometric parameters. [ABSTRACT FROM AUTHOR]

Aerodynamics of a soccer ball was studied with a three dimensional numerical approach using ANSYS Fluent. The ball used was a 32 panel soccer ball which was modeled in CAD and it was validated numerically by a 3D analyzing technique solving Reynolds-Averaged Navier Stokes (RANS) equations with k−ω BSL (Baseline) turbulence model. The flow was at zero angle of attack where velocity and spin conditions were varied to study the aerodynamic effects around the ball at different Reynolds Numbers and Spin parameters for rotation along two different axes. The validation procedure was able to predict the values of drag coefficient (Cd) reliably, it was also able to predict the wake structure along with velocity and pressure distribution. Both drag (Cd) and lift (Cl) coefficients were found to be highly dependent on spin parameter (Sp) values. The main limitation of the technique with the available computational resources was its inability to accurately predict boundary layer transition or growth, but despite this, several conclusions could be drawn regarding soccer ball aerodynamics. Spin parameter study contributes greatly to the technique of free kicks taken in the game of football. Exploitation of this phenomenon by players could have significant impact on the outcome of the game. [ABSTRACT FROM AUTHOR]

The light and medium sized trucks are the main backbone of freight movement in Bangladesh. Most trucks are typically box shape and built locally on imported chassis by roadside truck body builders with no consideration of aerodynamics, safety (crashworthiness) and environmental impact. Hence, the main purpose of this study is to analyze the aerodynamic aspect of light and medium sized trucks widely used in Bangladesh. The study involves the Computational Fluid Dynamics (CFD) modelling and experimental study using wind tunnel. The study also highlights the safety issues related to light and medium sized trucks. The findings reveal that minor changes in light and medium sized truck body design can reduce aerodynamic drag of nearly one-third thereby lowering fuel consumption and greenhouse gas emission. [ABSTRACT FROM AUTHOR]

Objective of review is to study tyre aerodynamics which aims to reduce emissions, fuel intake and to improve the efficiency of automobiles. Tyre is one of the most essential part of vehicle as it plays a major part in ensuring safety of the vehicle, aerodynamics of a rotating tyre contributes about 33% of total vehicle drag. Decrease in drag can lead to increase in safety, comfort and efficiency. Even a minute change in geometry of tyre can impact the vehicle drag by a minor amount. Friction of tyre is basis for control systems developed in improving safety at dangerous braking situation; parameters like load, velocity, and slip rate including pavement characteristics affect friction. Type of inflation affects consumption of fuel and determines life of tyre; properly inflated tyre is more efficient by reducing noise generation and fuel consumption therefore reducing environmental issues. In order to increase performance of vehicle advancement should be made in improving aerodynamics of a vehicle. Main intention of paper is to address the design of tyre for different vehicles providing idea for researchers and new learners to work on vehicle tyre aerodynamics. [ABSTRACT FROM AUTHOR]

Design optimization of the vehicle has been an integral part of Vehicle Aerodynamics. The reason so much heed is given to this research area is due to the ever-growing concern of detrimental effects of fuel on the environment. This paper aims to optimize the shape of auto-rickshaw which is one of the most widely used vehicles in India. Being the developing nation, people use auto-rickshaw because it is economical which makes it essential to modify the design to reduce drag. This, in turn, improves the fuel efficiency of the auto-rickshaw. The impact of the addition of diffuser at the underbody along with varying slant angle at the rear side to provide boot area is studied. The modifications are done on CATIA V5 followed by investigating the coefficient of drag on ANSYS Fluent. [ABSTRACT FROM AUTHOR]

A number of studies have been conducted on different flow control techniques in order to increase the aerodynamic performance of different airfoils. This study will be focusing on a passive blowing flow separation control technique known as 'vented airfoil'. Vents are designed inside the airfoil geometry in order to inject high momentum fluid from pressure surface into suction surface to manipulate the flow over the airfoil in order to delay the boundary layer separation. This paper will conduct a feasibility study of the vents in two different airfoils, namely, NACA2412 and NACA23012. The 2D model of the airfoils was developed with CATIA V5R20 and SST K-ω turbulence model was used for CFD analysis. The critical comparison between the resulting data of ventedNACA2412 and vented NACA23012 airfoils will be useful to determine the feasibility of the above mentioned stall delaying technique. [ABSTRACT FROM AUTHOR]

The present paper is about the aesthetic aerodynamics of fire spark arising out of corn grilling done at beaches in Chennai, India. The observations are recorded as videos and images via a camera. The pictures are analyzed for the flow features and physical insights were derived. The experimental setup and its working procedure was discussed in detail with schematic. The flow features are discussed in detail with the fundamental flow physics like "cross-flow". The techniques adapted for the production of fire spark is also discussed with positioning effects. The typical anticipated applications and suggestions are also provided. [ABSTRACT FROM AUTHOR]

The Aero-Aquatic vehicle or amphibious aircraft, a machine that runs in both air and inside water, it is a breakthrough in the application of aircraft and vehicle which runs underwater. By this, there will be a wide application advantage in defence and civil field, the research purpose is to design an underwater aircraft which could run efficiently in both air and water by using techniques like morphing wing, morphing tail and external ballistic tanks which makes the vehicle counterbalance from all the angles, the inclusion of bionics are there in this research, By taking consideration of sustaining UAV models, manned amphibious vehicles and morphing wing designs. The design was undergone both hydrodynamic and aerodynamic analysis to know the flow characteristic. The complete designing and analysis are done in AUTODESK & CFD-ANSYS to know accurate results. The air-water transition, the adaptive wing structure between air and water which is also known as morphing wing, the different propulsion type, and it also summarized the power source. Furthermore, the application scenario of bionics is summarized. It is challenging to satisfy the structural characteristic of aircraft due to the density of water. This research will answer the question regarding the co-relation between hydrodynamics and aerodynamics. Further research and development (R&D) is required to improve and implement the Aero-Aquatic vehicle. [ABSTRACT FROM AUTHOR]

Tuk Tuk is a common vehicle used by many people in various countries. The vehicle is designed for low and medium speeds due to the usage of small capacity engines for higher mileage purposes. The improvement in aerodynamic performance is the only way to improve the efficiency of the vehicle. To know about the aerodynamics, the present study focuses on the study of flow over the considered vehicle via drag with moment generation and flow visualizations. The results show the modifications done to the vehicle results in drag reduction [ABSTRACT FROM AUTHOR]

Bio Fluid Dynamics plays a major role in sports aerodynamics especially swimming, cycling, etc., the need for aerodynamic analysis is due to drag production and its impact on the timing consumed by the person during the race. This project considers a special nail for studying the flow structures formed by it when subjected to turbulent flow. The generation of vortices is visualized using a laser sheet. The results suggest that the vortices have an influence on the wake structure and it is also affected by the orientation of the nail. [ABSTRACT FROM AUTHOR]

Building Aerodynamics is the study of wind flow around a building. As a building is considered to be a bluff body an understanding of a flow around it will give an insight into the relation between geometry and wind flow pattern. The present study will focus on the numerical simulation of Tech Park, a high-rise building located in SRM Institute of Science and Technology. As the present work is also going to be conducted experimentally in the near future, a scaled down model of this building will be analysed on computation. The software used will be ANSYS fluent. A contour on the coefficient of pressure (Cp) with its lateral and longitudinal variations along the building is expected to be analysed, Flow visualisation in the front and wake region will also be highlighted upon. This numerical study will also be referenced to similar studies which will be conducted on the models of a cube and cuboid of similar dimensions of the building. This study can be used as a reference for the study of many high-rise buildings of similar shapes. It can also be used as a base of study in the fields of civil engineering and architectural aerodynamics. [ABSTRACT FROM AUTHOR]

Flow analysis is considered to be the most crucial procedure in aerodynamics. Analysis of flow and its parameters over any object has to be done with considering aerodynamic loading acting over it. In the field of aerodynamics, wind tunnel test setup is used for flow analysis. The wind tunnel test section should always afford a laminar and uniform flow to provide exact results during flow parameter determination. But attaining cent percent laminar flow inside a wind tunnel test section is practically not possible. Hence there is an immense requirement of performing calibration before starting any research experiments in a wind tunnel. It is to be noted that wind tunnel calibration is done with ultimate care to avoid any error in the analysis. Generally a Pitot - static probe is used to calibrate subsonic wind tunnel. But the Pitot - static tube has many limitations like single point data sensing. Hence a new efficient and compact instrument has to be developed for the calibration of wind tunnels. In this paper, a yaw sphere is designed and analyzed to perform the calibration of a subsonic wind tunnel. [ABSTRACT FROM AUTHOR]

Rectangular-to-Ellipse Shape Transition (REST) inlets are a kind of inward-turning inlets designed for hypersonic vehicles, especially under integration design backgrounds. The streamline tracing technique is an inverse method for designing inwardturning inlets by extracting different streamtubes from the same reference flow. In present work, the streamline tracing technique is coupled with an optimization procedure. The procedure for designing a REST inlet with prescribed mass capture at the design point and optimal performance is illustrated. [ABSTRACT FROM AUTHOR]

Flow separation from the wing surface imposes apparently the serious effect on aerodynamic characteristics, decreasing the lift and increasing the drug, so it is an undesirable phenomenon to be excluded. The baseline free stream disturbances (vortex, acoustic and vibration ones) may influence essentially on the flow topology and temperature distribution. The study of the key phenomena by Liquid Crystal Thermography under conditions of low subsonic velocities in the facility of ITAM SB RAS is presented. [ABSTRACT FROM AUTHOR]

The work is devoted to the development of a stand for physical modelling of the workflow and visualization of the gas flow in the flow cavity of a vortex jet device. Based on the literature review, a number of examples have been discovered on visualizing the working process in the flow cavity of a vortex jet device. The developed stand allows physical modelling of working processes in the flow cavity of a vortex jet device using its incomplete layout. Using similarity criteria, the developer can obtain the necessary parameters of the workflow in a real object of study. Also, the designed stand allows one to study the distribution of gas flows in the flow cavity of a vortex jet device. Studying the gas flow process in various models of vortex jet devices using the developed stand will allow the developer to draw a conclusion about the influence of the geometric parameters of the structure on the aerodynamics of the vortex chamber, as well as to study the gas flow in the flow cavity. The stand is recommended to be used as a tool in the design technique for vortex jet devices, which are based on multicriteria optimization of the geometric parameters of the flow cavity based on the zero-order method (Simplex method). [ABSTRACT FROM AUTHOR]

This study is aimed to obtain the optimal aerodynamics design for the student class formula car for the needs of the Formula Student Japan SAE competition, especially for dynamics events. To achieve these objectives, the following study steps are taken: evaluation of previous design, formulation of design concepts, referring event rules, designing, numerical simulations using CFD software packages, analysis, optimizing, and finalizing designs. Optimizing the undertray performance and analyzing the effect of DRS system is the main focus in this series of studies. The results show that the coefficient of lift is decreasing relatively with an increased undertray inlet angle. The lowest Cl value reached 0.203 with delta 24.25% at 20o undertray inlet. Drag force decreased drastically with the DRS system usage, up to 87% from 101.66 N to 12.86 N at 0o airfoil angle of attack. [ABSTRACT FROM AUTHOR]