Urban floods are very destructive and have significant socioeconomic repercussions in regions with a common flooding prevalence. Various researchers have laid down numerous approaches for analyzing the evolution of floods and their consequences. One primary goal of such approaches is to identify the areas vulnerable to floods for risk reduction and management purposes. The present paper proposes an integrated remote sensing, geographic information system (GIS), and field survey-based approach for identifying and predicting urban flood-prone areas. The work is unique in theory since the methodology proposed finds application in urban areas wherein the cause of flooding, in addition to heavy rainfall, is also the inefficient urban drainage system. The work has been carried out in Delhi’s Yamuna River National Capital Territory (NCT) area, considered one of India’s most frequently flooded urban centers, to analyze the causes of its flooding and supplement the existing forecasting models. Research is based on an integrated strategy to evaluate and map the highest flood boundary and identify the area affected along the Yamuna River NCT of Delhi. In addition to understanding the causal factors behind frequent flooding in the area, using field-based information, we developed a GIS model to help authorities to manage the floods using catchment precipitation and gauge level relationship. The identification of areas susceptible to floods shall act as an early warning tool to safeguard life and property and help authorities plan in advance for the eventuality of such an event in the study area.

In this research paper, we focus on creating a new winglet design to decrease vortex generation and consequently, reduce induced drag. This innovative winglet for aircraft wings helps improve overall efficiency. Winglets are aerodynamic components that are attached at the wingtips and play a crucial role in reducing drag and minimizing vortex formation, such as tip vortices, thus enhancing fuel economy. The main objective of this research paper is to mitigate the hindering effect on aircraft performance, namely, the reduction of detrimental vortices. The methodology of this research paper involves the use of software like CATIA for design and ANSYS software for analysis. The design process includes the creation of different design iterations of winglet designs with specific parameters, intending to reduce vortex formation and increase lift. Subsequent analyses were conducted on each design iteration to test performance, lift, and drag variations using ANSYS software. The results of analysis will be presented, highlighting the performance of each winglet design in comparison to the baseline wing. The study aims to identify the most efficient winglet design, aiming to minimize vortex and drag generation while maximizing lift and other aerodynamic parameters to increase overall efficiency. The study's implications will be explored for aircraft manufacturers and operators, including the potential benefits of fuel savings and a positive environmental footprint. This research significantly contributes to the aircraft domain by offering insights into innovative winglet design formulations capable of enhancing aircraft performance. This investigation serves as a foundation for further research in the realm of winglet design to enhance the sustainability and efficiency of future aircraft.

In this paper, a idea of having a streamlined hollow shape is introduced to the basic NACA airfoil namely, NACA 0018, which is symmetrical along the chord. To obtain detailed information about the pressure, lift, drag, and velocity distribution over the airfoil, along with the coefficient of lift and drag forces, I used popular advanced software such as Catia for design and modelling, structural sizing was also done in Catia, aerodynamic meshing was done in ANSYS fluent, it also helped me to obtain flow solutions. The optimization of the wing is to reduce the weight of the wing along with some decrease in the negative lift for the negative angle of attack of the wing with approximately small decrement in drag for positive angle of attack. Therefore, according to the Breguet equation, there will be the increase in range. According to the power and effective coding of the ANSYS and CATIA, I obtained increase in range in the domain of negative angle of attack. The second most effective thing is that I reduced the planform area but assumed to be constant due to negligible increment. The freestream velocity has been taken as 30 meters per second which comes in the domain of subsonic flight considerations.

This paper presents a comprehensive study on path planning and optimization for unmanned aerial vehicles (UAVs) in different applications. It combines the findi This paper presents a comprehensive study on path planning and optimization for unmanned aerial vehicles (UAVs) in different applications. It combines the findi