Aerodynamic design of aircraft

In recent years, the global petroleum energy crisis has driven the automotive manufacturing industry to focus on reducing the aerodynamic drag coefficient through optimized design to improve fuel economy, and this demand is particularly prominent in the field of large buses. This paper takes three large buses with different shapes as the research objects, and explores the variation law of their aerodynamic characteristics through streamlined modification of the body shape. In the study, first, a 3lD base model of the large bus was constructed, and three groups of large bus models with different shapes were generated by adjusting the shape parameters. Subsequently, under unified boundary conditions (such as inflow velocity, ambient pressure, etc.), computational fluid dynamics (CFD) methods were adopted, and simulation experiments were carried out with the help of Fluent software. Data such as gas flow field diagrams of each group of models were obtained through numerical simulation, and the influence of different shapes on the aerodynamic drag coefficient was compared and analyzed.The results show that large buses with streamlined designs at the front and rear have better aerodynamic characteristics, and the effect in reducing the drag coefficient is more significant. At the same time, this study can provide a reference basis for the aerodynamic optimization design of large buses.

Multi-element airfoils are high-lift devices and provide improved aerodynamic characteristics, which are beneficial for several applications. The performance of high lift devices was investigated numerically by adapting the 2D viscous, steady, pressure model equations together with the SST k-ω turbulence model. Simulations were performed using ANSYS Fluent 24 for the NHLP2D airfoil with a leading edge slat and trailing edge flap. The flow is considered at a Reynolds number of 1.6x10 5 and varying angles of attack from 0 to 28 deg. The parameters that describe the positioning of the slat and flap were tested variables. These variables include deflection angles, gaps, and overlaps. The lift and drag coefficients are evaluated for various configurations. The results reveal that slats increase the maximum lift on the wing and delay stall, increasing the maximum angle of attack. However, they reduce the lift. In contrast, the flaps increase the overall high-lift configuration airfoil camber, thereby increasing lift. It was found that for the tested slats and flaps locations, slats with a 2.6% gap,-1.5% overlap and 30° deflection, and flap with a 1.3% gap, 5.3% overlap and 30° deflection was the one with the most favorable performance, generating a 𝐶𝑙 𝑚𝑎𝑥 of 3.81 and 𝐶𝑑 of 0.158.

An optimal sensor placement methodology is implemented and herein proposed for SHM model-assisted design and analysis purposes. The kernel of this approach analysis is a genetic-based algorithm providing the sensor network layout by optimizing the probability of detection (PoD) function while, in this preliminary phase, a classic strain energy approach is adopted as well established damage detection criteria. The layout of the sensor network is assessed with respect to its own capability of detection, parameterized through the PoD. A distributed fiber optic strain sensor is adopted in order to get dense information of the structural strain field. The overall methodology includes an original user-friendly graphical interface (GUI) that reduces the time-to-design costs needs. The proposed methodology is preliminarily validated for isotropic and anisotropic elements.

In this study, flutter analyses are performed for generic adaptive camber wings with hingeless trailing edge control surfaces. These control surfaces operate based on a concept that exploits the controlled flexibility of the semi-open secondary wing structure. By introducing structural modifications that allow for chordwise sliding between upper and lower skin panels, positive or negative camber changes may be realized for the wing. Using MSC® PATRAN package, wing finite element models are created. In these models, components of the adaptive camber wing, i.e. front and rear spars, spar caps, skins, ribs, stringers and control bars are defined as separate property regions. In order to model the hingeless control surfaces, multi-point-constraints (MPC) are used to represent the sliding action, as well as the interactions between several components. In aeroelastic models created using MSC® FLDS, structural and aerodynamic degrees-of-freedom (dof) are coupled to each other using infinite plate spline functions. The unsteady aerodynamic loads are represented using the Doublet-Lattice Method (DLM). In numerical analyses performed, two different wing configurations are considered, namely Wings A and B. In Wing A, a single hingeless control surface extends throughout the full wing span. Wing B has the same structural properties as Wing A, except for the hingeless control surface, which is split into two equal sized parts. The results of the free vibration analyses show that for both wing configurations, the control surface motion is highly coupled to the bending and torsion type global modes. Furthermore, in the second configuration, additional local modes are observed for the control surface. As a final study, p-k method is employed to calculate flutter speeds for Wings A and B and to identify the modes of instability.

This project highlights the different steps of a UAV design (fixed wing) to obtain a good model or prototype that will fly and fulfill its specific mission. Generally, it consists of estimating some initial values relying on some minor UAV historical data that will be checked and corrected by the end to optimize the results following an algorithm that every single aerospace engineer can use to realize an FWD with the most straightforward method. Our paper goes through all the steps one by one by providing some details and clarifying any challenge we will encounter in realizing the prototype. The challenge is not limited to the design and optimization part, but it will extend to the manufacturing part in which we are supposed to choose the materials and the manufacturing processes, this adds more intensity to the project because of the limitations that we will face at that level this paper we will use all the expertise that we gathered from a previous project of design that we have realized and the knowledge that we have enhanced in the past years of study at UIR in aerospace and fluid sections The paper is globally summing up conceptual design ,energy optimization, and stability assurance this by integrating analytical methods ,modelling using some advanced software (XFLR5, CATIAV5),and simulation techniques .During this investigation, we aim to add our prototype to the existing realized UAVS so that we enlarge the historical data that are available about UAVS and to facilitate any upcoming innovation in that domain by finding the best design in term of energy saving and performance.

This report presents the design and conceptual development of a revolutionary aerial platform The DroneCarrier Prototype invented by Mario Arturo Ruiz Estrada. The DroneCarrier (See Figure 1) redefines unmanned aerial vehicle (UAV) operations by integrating a multipurpose launch, command, and support platform capable of floating in atmospheric space. Designed for defence, surveillance, humanitarian aid, and experimental aerospace operations, the DroneCarrier introduces a new era in aerial logistics and airborne warfare strategy. This report explores the technical specifications, functionalities, and potential applications of this innovative structure.

Makalah ini membahas proses pembuatan pesawat model Chuck Glider (Outdoor Hand Launch Glider/OHLG) dengan menggunakan kayu balsa sebagai bahan utama. Penelitian ini bertujuan memberikan panduan teknis sekaligus menguji performa hasil rakitan melalui eksperimen sederhana berupa pengukuran waktu dan jarak luncur. Hasil menunjukkan bahwa desain yang akurat terhadap airfoil dan titik pusat gravitasi (CG) sangat memengaruhi kinerja terbang glider.

The Aerodynamic Multi-Levels Wingtip is an advanced wingtip configuration designed to optimize airflow efficiency and reduce aerodynamic drag in modern aircraft. Unlike conventional single-plane winglets, this innovative design incorporates multiple vertically or laterally staggered surfaces that manipulate wingtip vortices more effectively, leading to enhanced aerodynamic performance. This system is engineered to reduce induced drag, improve the lift-to-drag ratio, and increase fuel efficiency across various flight regimes. Constructed from lightweight composite materials such as carbon fiber-reinforced polymers, it is suitable for both new-generation aircraft and retrofitting on existing platforms. The design may also include optional features such as embedded sensors, active flow control elements, and nano-wing devices to further improve aerodynamic responsiveness. Overall, the Multi-Levels Wingtip concept offers a sustainable, high-performance solution for the aerospace industry, contributing to lower emissions and better operational efficiency without compromising structural integrity or manufacturability.

In low speed collisions, insurance cost is a factor which is taken into account as a design criterion to reduce structure damage and fixing cost. In this study, it is focused on the applied permanent damages of vehicle frontal door caused by pole impacts. In the side impact, the side door beam is responsible to absorb the most possible kinetic energy. Two significant parameters including material and geometry of a side door beam are discussed here to reduce permanent damage of the door. To study the effect of material as the first phase, six different sheets of material have been concerned to investigate the rigidity of the structure. For the second phase, geometry modification of the side door beam has been performed via creating new CAD-reinforcing ribs. Consequently, the strength in elasto-plastic mode, maximum deflection and plastic strain of the equipped system representing the permanent damage is obtained in order to achieve lower losses.

As more people travel by air, the aviation sector is feeling increased pressure to reduce its environmental impact. If sustainability becomes a part of aircraft management, efficiency in operations can be linked with protecting the environment. This document analyzes how aircraft companies can manage their fleets in a more sustainable way, using energy-saving technologies, arranging flights wisely and opting for environmentally friendly maintenance. Relying on advanced ways to analyze data, as well as using alternative fuels and more efficient logistics, these services are able to greatly reduce both their carbon footprint and any waste produced. Operators are using SAFs and electric or hybrid propulsion to keep their airlines profitable, as these approaches are needed to meet the strict guidelines set by authorities. Besides, when aircraft components are recycled and greener supply chains are used, the efficiency of resource use increases. To make progress, it is important to cooperate with agencies, manufacturers and airport authorities. The study also details how top aircraft management companies have included sustainability and achieved reductions in fuel usage and emission levels. Emphasizing sustainable actions, aircraft management providers contribute to worldwide efforts to manage climate change and gain an edge over other companies in the industry. The article stresses the need for urgent green practices and helps operators understand how to make their operations eco-friendly.

Summary The theory of torsion of thin walled beams of open cross-sections with influence of shear on the basis of the classical Vlasov’s theory of thin-walled beams of open cross-sections for beams with single and double symmetrical cross-sections is developed. It is proved that the beam subjected to torsion with influence of shear exerted by couples in the beam crosssections is also subjected to bending due to shear in the plane orthogonal to the plane of symmetry. The beam is subjected to torsion with influence of shear only in the case of double symmetrical cross-sections. The principal cross-section axes as well as the principal pole are defined according to the classical theory of thin-walled beams of open sections. Illustrative examples are given, as well as a comparison with the finite element method.

In this study, the effect of single and double synthetic jet actuators on the aerodynamic efficiency of the airfoil wing of a maneuverable aircraft has been numerically investigated using fluent software. The flow around the airfoil has been solved using the turbulent unsteady Reynolds-averaged Navier-Stokes equations with k-ε Turbulence model in Fluent software. Investigations have been carried out at a Mach number of 0.15 (corresponding to a Reynolds number of two million) and at angles of attack from 0 to 19 degrees. The grid with 106469 elements is organized so that the y+ parameter on the airfoil boundary is in order 1 to discretize the computational domain. In these investigations, the single and double synthetic jet actuators are placed in different positions on the upper surface of the airfoil to obtain the most suitable position in terms of the best aerodynamic efficiency. The results of this numerical study showed that for a single synthetic jet, the highest aerodynamic efficiency value of the synthetic is in the 8.63% chord from the airfoil leading edge. Because in this position, the size of the separation bubble on the airfoil becomes smaller. Also, for the double synthetic jet, the highest aerodynamic efficiency is obtained in the synthetic jet positions of 8.63% and 12% chord from the airfoil leading edge. The highest percentage increase in single jet mode is 23.72%, and in double jet mode, it is 27.4%.

This paper contain the content of basic review of an aircraft fuel system .This paper cover the various fuel system and fuel subsystem used in aircraft .Purpose of an aircraft fuel Sub system to monitors the fuel supply, its control, storage, drainage and also maintain stability of aircraft.. Basically the purpose of fuel system is to supply the fuel in all phase of including landing ,takeoff, Banking and sharp maneuvering fuel system should also supply the sufficient amount of neat and clean fuel at required pressure. Types of fuel system may vary in aircraft but all the aircraft keeps their own fuel system. The fuel system must be used keeping the centre of gravity to be stable in mind.

In contemporary architecture there is an increasing demand for transparency and curved shape. The Cold-Bending process is an effective and relatively inexpensive way of creating double curved surface glass. This thesis focuses on the shaping of a plate with the application of an out-of-plane displacement at its corner, also called cold-warping.

Summary The theory of torsion of thin walled beams of open cross-sections with influence of shear on the basis of the classical Vlasov’s theory of thin-walled beams of open cross-sections for beams with single and double symmetrical cross-sections is developed. It is proved that the beam subjected to torsion with influence of shear exerted by couples in the beam crosssections is also subjected to bending due to shear in the plane orthogonal to the plane of symmetry. The beam is subjected to torsion with influence of shear only in the case of double symmetrical cross-sections. The principal cross-section axes as well as the principal pole are defined according to the classical theory of thin-walled beams of open sections. Illustrative examples are given, as well as a comparison with the finite element method.

Hydraulic systems in aircraft provide a means for the operation of aircraft components. The operation of landing gear, flaps, flight control surfaces, and brakes is largely accomplished with hydraulic power systems. Hydraulic system complexity varies from small aircraft that require fluid only for manual operation of the wheel brakes to large transport aircraft where the systems are large and complex. To achieve the necessary redundancy and reliability, the system may consist of several subsystems. Each subsystem has a power generating device (pump) reservoir, accumulator, heat exchanger, filtering system, etc. System operating pressure may vary from a couple hundred pounds per square inch (psi) in small aircraft and rotorcraft to 5,000 psi in large transports.

Original scientific paper The paper is focused on the preliminary aerodynamic analyses of a new light aircraft in symmetrical flight configurations. Initial calculations have been done using a 3D vortex lattice method. Since this method is based on inviscid flow concept, the non-linear calibration diagrams for the effectiveness and circulation of control surfaces have been derived from wind tunnel test data of an existing airplane. These calibration functions have been interpolated for a new light aircraft geometry, and analyses of lift and moment coefficients with different flaps and elevator deflections have been performed. Deflected flaps and elevator generate local lift redistributions which contribute to the induced drag, even at angles of attack when the total airplane lift is zero, which has been successfully determined by the applied CFD model. Parasite drag components, omitted by CFD calculations, have been obtained using DVL and Datcom methods and superimposed with CFD results, giving complete new aircraft polars, which have been successfully applied in longitudinal stability and basic performance estimates.

Original scientific paper The paper is focused on the preliminary aerodynamic analyses of a new light aircraft in symmetrical flight configurations. Initial calculations have been done using a 3D vortex lattice method. Since this method is based on inviscid flow concept, the non-linear calibration diagrams for the effectiveness and circulation of control surfaces have been derived from wind tunnel test data of an existing airplane. These calibration functions have been interpolated for a new light aircraft geometry, and analyses of lift and moment coefficients with different flaps and elevator deflections have been performed. Deflected flaps and elevator generate local lift redistributions which contribute to the induced drag, even at angles of attack when the total airplane lift is zero, which has been successfully determined by the applied CFD model. Parasite drag components, omitted by CFD calculations, have been obtained using DVL and Datcom methods and superimposed with CFD res...

Iki eksenli gerilme yapılan tasarımın daha dayanıklı ve güvenli olabilmesi için hangi malzemeyi kullanmamız gerektiği ile ilgili kararları verebilmek için hesaplanır. Hesaplamalar sonucunda analizini yapıp gerekli iyileştirmeleri yapmak gerekir. Uçak mühendisliği için de uçak tasarlarken özellikle uçak gövdesi, kanatları, kuyruk kısmı, iniş elemanlarının dayanıklılığını test etmek için hesaplarız. Kullandığımız malzemenin dayanıklı olabilmesi akma dayanımını ve elastik sınırları geçmemesi gerekir.

Along with the rapid development of technology, the use of active-type aerodynamic components is widely applied in automobiles. One of the aerodynamic components is dynamic spoiler. Dynamic spoiler is a type of spoiler that has synergy when a car is braking and turning and can also operate simultaneously. This study is aimed at designing a dynamic spoiler mechanism that can be put on car with a maximum rotation angle of dynamic spoiler movement of 15° from its normal condition when a car is braking or turning. The proposed dynamic spoiler employs an electrical system with a servomotor that produces a torque of 1.8 N.m as its actuator. The input of steering wheel angle is converted to the movement of potentiometer as a steering wheel movement controller while a push button mechanism that is controlled by the Arduino microcontroller is used for the input of brake pedal. The test results demonstrate that when the steering wheel rotates 90° the rotation angle of the spoiler moves 14.7° ...

Seiring dengan perkembangan teknologi yang semakin cepat, penggunaan komponen aerodinamika tipe aktif mulai banyak diterapkan pada mobil. Salah satunya adalah spoiler dinamis. Spoiler dinamis adalah suatu tipe spoiler yang memiliki sinergitas ketika mobil melakukan pengereman maupun gerakan membelok serta dapat juga bekerja secara simultan. Penelitian ini bertujuan untuk merancang mekanisme spoiler dinamis yang dapat diterapkan pada mobil dengan sudut putar pergerakan spoiler dinamis maksimal sebesar 15° dari kondisi normalnya ketika mobil melakukan proses pengereman maupun proses membelok. Spoiler dinamis yang diusulkan memanfaatkan sistem elektrik dengan motor servo yang mempunyai besaran torsi 1.8 N.m sebagai aktuatornya. Input sudut roda kemudi diteruskan menjadi pergerakan potensiometer sebagai pengatur gerakan roda kemudi sedangkan input pedal rem menggunakan mekanisme push button yang dikendalikan oleh mikrokontroler Arduino. Hasil pengujian menunjukkan bahwa ketika roda kemu...

This research focuses on assessing and enhancing the performance of the MQ-1 Predator aircraft, considering aspects such as design and manufacturing. The design was created utilizing Fusion 360, and aerodynamic performance aspects were evaluated using ANSYS software. Computational models were employed to ascertain the aerodynamic characteristics of the baseline design and investigate modifications aimed at achieving optimal design and performance.

The present paper summarizes the key findings of a numerical study on the aerodynamic behavior of a generic light aircraft under flow conditions, which are typically associated with spin motions. These conditions include high angles of attack, crosswind and rotational motion. Besides investigating the limits of Reynolds-averaged Navier-Stokes simulations for this type of conditions, the simulations contribute to a better understanding of existing wind-tunnel data. Furthermore, the influence of wind-tunnel related aspects such as scaling effects are investigated. The comparison between the numerical and experimental results generally shows good agreement regarding global force coefficients and separation behavior. The characteristic behavior with regards to crosswind and rotational motion around the longitudinal wind axis is captured well by the computations. Scaling effects are considerable with the maximum vertical force coefficient increasing by up to ∆C Z,max = 0.25 at real flight Reynolds and Mach number compared to wind-tunnel conditions.

Space exploration has advanced much further chief of all advancements made in rocketry. AI is
important in the rocket’s launch and landing in that they are able to improve on the existing systems. This
paper provides a critical discussion on the incorporation of AI technologies into these systems with reference
to effectiveness, safety, and mission accomplishment. Algorithms become an efficient way to assist decisions in
launch phases, to specify trajectories and to tweak auto-landing systems. Modern complex systems can be
analyzed by means of machine learning and neural networks, resulting in improved prediction of system
health and less maintenance failures. In addition, I believe that it is crucial that AI is used in controlling
reusability of rockets so as to remove human factor and at the same time bring in efficiency. The audit shows
that AI-powered algorithms have enhanced the launch accuracy up to 15% and minimized system failures up
to 10%. AI based autonomous landing systems have reported a 20% improvement in the accuracy of landing thereby reducing lifecycle risks and improving the reusability of rocket stages. It has been marked that integration of AI for diagnosing problems results in 25% overall system reliability therefore the study supports the statement. It has also enhanced the optimization of fuel, which is critical for mission sustainability, through a 12% improvement on fuel efficacies.

Katmanlı kompozit yapılar, mukavemet/ağırlık oranlarının yüksek olması nedeniyle havacılıkta yoğun kullanım alanı bulmaktadır. Bu yapılar, ses üstü süratlerde uçan hava taşıtlarında sonik patlamalara veya civarlarında meydana gelen patlamalardan dolayı anlık basınç yüklerine maruz kalabilmektedirler. Söz konusu yapı elemanları ani yükler altında büyük hasarlar görebilmektedir. Bu yüzden yapıların bu yüklemeler altında nasıl davranacağının önceden bilinmesi önemli bir konudur. Bu tez Devlet Planlama Teşkilatının 901341998k121980 numaralı "Yapılar Üzerindeki Patlama Etkilerinin Araştırılması" adlı projesinin bir parçasıdır. Sonuçların bir kısmı bu proje kapsamında yayınlanan raporda da sunulmuştur. Tezin her aşamasında rehberliğini ve değerli vaktini benden esirgemeyen sayın hocam Prof. Dr. Zahit MECİTOĞLU'na, fikirleri ile tezin gelişmesine katkıda bulunan hocalarım Prof. Dr. Süleyman TOLUN ve Prof. Dr. Mehmet Hakkı OMURTAG'a ve yetişmemde emeği olan tüm hocalarıma, ihtiyacım olan vaktin sağlanmasında her türlü kolaylığı gösteren değerli komutanım Hv.Müh.Yb. İsmail KILINÇ'a ve onun nezdinde sıralı tüm komutanlarıma en içten saygı ve sevgilerimi sunarım. Çalışmalarım esnasında benden hiçbir zaman desteğini esirgemeyen sevgili eşim Selcen YAROĞLU KAZANCI'ya teşekkür ederim.

Bilinen izontropik gaz denklemi bugüne kadar çeşitli formülasyonlarda gazlar için kullanılmıştır. Bu çalışmada, ani yüklemeye maruz içi kum dolu bir silindir-piston sistemindeki basınç dağılımı kumun gaz gibi davrandığı kabulü altında teorik olarak incelenmekte ve nümerik sonuçlar elde edilmektedir. Formülasyonda geçen γ katsayısı deneysel olarak belirlenmek kaydıyla bu çalışmanın sonuçları, metalürjide kullanılan tozların sıkışma sırasındaki davranışlarının incelenmesinde de kullanılabilir.

We know that a missile launch from a satellite can produce a huge amount of reaction force. In this paper we analyses the impact of such force on a satellite body in space orbiting around the earth. The satellite in orbit must be stabilized and unperturbed. Actuators and reaction thrusters are used to stabilize the satellite body according to the mission objectives. The concept of two body problems and orbital transfer applied over this problem to analyze the change in the attitude of the satellite and the concept of Kepler's third law can be used to find the time period for the satellite to return to its original orbital position. This paper identifies the final satellite attitude in terms of orbit distance & velocity after the missile launch impact and time period for return to the initial position.

HAL is a multidisciplinary open access archive for the deposit and dissemination of scientific research documents, whether they are published or not. The documents may come from teaching and research institutions in France or abroad, or from public or private research centers. L'archive ouverte pluridisciplinaire HAL, est destinée au dépôt et à la diffusion de documents scientifiques de niveau recherche, publiés ou non, émanant des établissements d'enseignement et de recherche français ou étrangers, des laboratoires publics ou privés.

The knowledge of flow behavior and associated aerodynamic characteristics are important in the design and analysis of a multi-stage launch vehicle. A typical launch vehicle in flight passes through denser layers of atmosphere covering both subsonic and supersonic Mach numbers. Aerodynamic coefficients are important inputs for trajectory simulation, performance analysis and control system design of a launch vehicle. A multi-stage launch vehicle with strapons is a complex configuration to study the flow behavior over it. Generally extensive wind tunnel testing is done to understand the flow characteristics of such a configuration. With the current popularity of Computation Fluid Dynamics (CFD) as a powerful design tool, it is appropriate to make use of its technology to understand the complex flow behavior over a multi-stage launch vehicle with strapons. Most present day launch vehicles have either solid or liquid strapons to meet the mission requirements

Air Defense Systems contain high-value assets that are expected to fulfill their mission for several years-in many cases, even decades-while operating in a fast-changing, technology-driven environment. Thus, it is paramount that decision-makers can assess how effective an Air Defense System is in the face of new developing threats, as well as to identify the bottlenecks that could jeopardize the security of the airspace of a country. Given the broad extent of activities and the great variety of assets necessary to achieve the strategic objectives, a systems approach was taken in order to delineate the core requirements and the physical architecture of an Air Defense System. Then, value-focused thinking helped in the definition of the measures of effectiveness. Furthermore, analytical methods were applied to create a formal structure that preliminarily assesses such measures. To validate the proposed methodology, a powerful simulation was also used to determine the measures of effectiveness, now in more complex environments that incorporate both uncertainty and multiple interactions of the entities. The results regarding the validity of this methodology suggest that the approach can support decisions aimed at enhancing the capabilities of Air Defense Systems. In conclusion, this paper sheds some light on how consolidated approaches of Systems Engineering and Operations Research can be used as valid techniques for solving problems regarding a complex and yet vital matter.

Sophisticated numerical simulations like finite element analysis (FEA) involve a complicated process from model setup to post-processing tasks that require replication of time-consuming steps. Utilizing FEA automation program simplifies the complexity of the involved steps while minimizing human errors in analysis set up, calculations, and results processing. One of the main challenges in designing FEA automation programs is to identify user requirements and link them to possible design alternatives. This paper presents a decision-making framework to design a Python based FEA automation program for modal analysis, frequency response analysis, and random vibration fatigue (RVF) analysis procedures. Analytical hierarchy process (AHP) and technique for order preference by similarity to ideal solution (TOPSIS) are applied to evaluate design alternatives considering the feedback received from experts and program users.

The wing of a fighter aircraft has various structural members which support aerodynamic and inertial loads, and transmit these loads to the fuselage. As a foremost step to evaluate the structural behaviour of the wing assembly, component contribution analysis is carried out. A finite element analysis of wing tulip of fighter aircraft isolated from the wing was performed under the design load case. Since aircraft wing is a statically indeterminate structure, reaction forces and moments at the supports depend upon the stiffness characteristics of the wing itself. In addition, stiffness of wing also affects the distribution of load and resulting deformation of the wing. These require that support structure of tulip isolated from the global wing model is represented by appropriate boundary conditions for the analysis. A comparative study for three boundary conditions (fixed support, nodal displacements and elastic support) was carried out to determine the representative boundary
condition for the analysis of structural members isolated from the global model. It was found that elastic support represents the stiffness of the global model and is a more appropriate boundary condition for the analysis of local models which are isolated from a global model.

The results from calculating the apogee altitude for different 1u configuration payloads show that the maximum altitude expected is 21,000 ft. for a 1U payload and 11,000 ft. for a 6U payload. The motor chosen for the launch is the Pro 150 O5800 White Thunder with a total impulse of 30,601 Ns, average thrust of 5,802 N, and burn time of 5.27 seconds. OpenRocket software was used to simulate the flight profile and the loads expected during the launch. Previous Work

Abstrak Penelitian ini menggunakan desain penelitian treatment by level 2x2. Sampel terdiri dari 36 siswa. Teknik analisis data adalah analisis varians dua jalur (ANAVA) dan selanjutnya dilanjutkan dengan uji Tukey pada tingkat signifikansi α = 0,05. Hasil penelitian ini menunjukkan bahwa (1). Nilai keterampilan renang gaya punggung pada perlakukan metode latihan bagian (A1) lebih tinggi dari nilai metode latihan keseluruhan (A2) siswa ekstrakurikuler renang SD Islam Al-Azhar Kelapa Gading Jakarta Utara (2). terdapat interaksi antara metode latihan (A) dan kecemasan (B) terhadap keterampilan renang gaya punggung siswa ekstrakurikuler renang SD Islam Al-Azhar Kelapa Gading Jakarta Utara. (3). Nilai keterampilan renang gaya punggung pada perlakuan metode latihan bagian kecemasan tinggi (A1B1) lebih baik dari nilai metode latihan keseluruhan kecemasan tinggi (A2B1) di ekstrakurikuler renang SD Islam Al-Azhar Kelapa Gading Jakarta Utara. (4). Nilai keterampilan renang gaya punggung pada...

The widespread adoption of Unmanned Aerial Vehicles (UAVs) can be traced to its flexibility and wide adaptability to various operating conditions and applications, comparably low cost of construction and maintenance and environmental friendliness as they can be easily configured for electric power. The use of electric power also favours its low noise applications such as surveillance. A major issue associated with surveillance, as addressed in this study is the compromise between Range and Endurance operation modes. The Range mode relates to being able to cover longer distances while the Endurance mode relates to spending longer times in the atmosphere for a fixed charge. Trying to balance the interplay of these parameters gave rise to a multi-objective optimization where the objectives are somewhat conflicting. This resulted in a set of Pareto solutions which are a set of design parameters (primarily angle of attack) that satisfy the joint requirements of the performance parameters of Range and Endurance. This study first considered a baseline aerodynamic design using traditional design methods. Design of Experiment techniques were then used to select the most favourable design points. This model was then used to build an input framework for Genetic Optimization algorithm deployed in the Global Optimization Toolbox of MATLAB. The result of this research shows that most of the region associated with medium angle of attack (AOA) setting (7 degrees) jointly satisfies good Range and Endurance performances with an average lift-to-drag ratio of 20 in the flight configuration considered. The implication of this result is that low velocity drag encountered in surveillance that requires a high AOA is largely reduced with the medium setting, albeit stabilized with other structural and aerodynamic settings, namely an aspect ratio of 13 and a taper ratio of 0.6.

Article history: Received 31 January 2019 Received in revised form 21 February 2019 Accepted 4 March 2019 Available online 22 March 2019 This paper is dedicated towards the design and fabrication of a mini sailplane with the aim of maximizing the glide ratio CL/CD. And at the same time minimizing the weight of the plane. For this NACA 7037 airfoil was selected for subsonic domain corresponding to low Reynolds number varying within the range of 105 to 3×105 as per the recommendations from literature [1]. A cambered NACA 7037 was fabricated from the wooden material and was experimentally investigated with different range of velocities and angle of attack for coefficient of lift and drag using wind tunnel setup. The same was numerically investigated using the commercial Finite Element Analysis FEA code of ANSYS FLUENT®. The results compared very well with the experimental one, thereby validating the computational fluid dynamics CFD model. This CFD model was applied to mini sailplane wh...

An exposition of Bernoulli's Theorem is made, including the differential and integral approaches. Compressible and incompressible, viscous and non-viscous flows are included. In the integral approach, a stream tube is treated and global quantities are defined particularly for the viscous terms without wall slip. In duct flow, a description of flows in laminar and turbulent regimes is made.

As we know that fixed wing unmanned aerial vehicle required long runways for takeoff and landing and also flight time then other. As it is difficult to have longer runway in city area, the need of vertical takeoff and landing (VTOL) arises. VTOL aircraft is the type of flight systems which have the ability to take off and land vertically, then transition to horizontal flight, and also allowing an aircraft to cover long distances at high speed and also have advantage to takeoff and land in vertical manner without the need of runway. There are various applications of VTOL such as it can be used as ondemand air mobility, for cargo and package delivery, in healthcare applications, and in emergency services. The new and emerging trends of VTOL are that it can be use as air ambulance. Air Ambulance service is a board term that combines two meaning i.e. air transport with basic emergency medical services which is able to transport injured patients or sick patients to the healthcare facilities and from healthcare facilities. So, in other terms, we can say that it is basically like airlifting patients in case of emergencies. Here, we are focused to develop advance VTOL air ambulance which can be use in any condition and which are capable to carry out its work more precisely and efficiently.

We know that a missile launch from a satellite can produce a huge amount of reaction force. In this paper we analyses the impact of such force on a satellite body in space orbiting around the earth. The satellite in orbit must be stabilized and unperturbed. Actuators and reaction thrusters are used to stabilize the satellite body according to the mission objectives. The concept of two body problems and orbital transfer applied over this problem to analyze the change in the attitude of the satellite and the concept of Kepler's third law can be used to find the time period for the satellite to return to its original orbital position. This paper identifies the final satellite attitude in terms of orbit distance & velocity after the missile launch impact and time period for return to the initial position.

Proper maintenance and continuous monitoring are essential for ensuring the safety of the structure. Many types of sensors are developed to monitor the degradations of the structure, especially in a harsh environment, to identify the structural defect at a preliminary stage. To consider the material as a sensor in a harsh environment should have the ability to withstand high temperatures or at a high vibration, electromagnetic interference, high strain, etc. The data acquisition technique and an optimum number of the sensor to get accurate data are a significant factor for SHM, especially at the harsh environment. This review will describe the different types of harsh environments and the suitable and application of reliable, high-efficiency sensors based on the harsh environment.

We know that a missile launch from a satellite can produce a huge amount of reaction force. In this paper we analyses the impact of such force on a satellite body in space orbiting around the earth. The satellite in orbit must be stabilized and unperturbed. Actuators and reaction thrusters are used to stabilize the satellite body according to the mission objectives. The concept of two body problems and orbital transfer applied over this problem to analyze the change in the attitude of the satellite and the concept of Kepler's third law can be used to find the time period for the satellite to return to its original orbital position. This paper identifies the final satellite attitude in terms of orbit distance & velocity after the missile launch impact and time period for return to the initial position.

A NACA 6-series Laminar flow airfoil, which at present is the most widely preferred choice on all modern high subsonic and transonic commercial passenger aircrafts has been taken for our study. The flow of air over the straight wing and swept back wings designed using the chosen airfoil cross section is simulated computationally with the CFD tool FLUENT. The wing, initially kept at zero sweep back angle, is analyzed at different Mach numbers ranging from 0.6 to 1.2 and the values of CL and CD are calculated. The same wing is then analyzed at five different sweep back angles via, 25o, 30o, 35o, 40o, 45o at various Mach numbers ranging from 0.6 to 1.2, and the values of CL and CD are calculated. The comparison made between the straight and swept back wings clearly depicts that there is a remarkable reduction of drag coefficient. Keywords—NACA-6 series; CFD; Sweep back angles; drag coefficient; lift coefficient.

Wind power is the source of propulsive energy for sailboats and albatrosses. We present the UNAv, an Unmanned Nautical Air-water vehicle, that borrows features from both. It is composed of a glider-type airframe fitted with a vertical wing-sail extending above the center of mass of the system and a vertical surface-piercing hydrofoil keel extending below. The sail and keel are both actuated in pitch about their span-wise axes. Like an albatross, the UNAv is fully streamlined, high lift-to-drag ratio and generates the gravity-cancelling force by means of its airborne wings. Like a sailboat, the UNAv interacts with water and may access the full magnitude of the wind. A trim analysis predicts that a 3.4-meter span, 3 kg system could stay airborne in winds as low as 2.8 m/s (5.5 knots), and travel several times faster than the wind speed. Trim flight requires the ability to fly at extreme low height with the keel immersed in water. For that purpose, a multi-input longitudinal flight controller that leverages fast flap actuation is presented. The flight maneuver is demonstrated experimentally.