2026· International journal of research and innovation in social science· Vol 10, pp. 1840-1846· 0 citations
Abstract
Driven by the growing demand for efficient emergency Vertical Takeoff and Landing (VTOL) transportation and advanced air mobility, the development of lightweight flying vehicles has become increasingly critical. This research presents an innovative flap design integrated with a jet engine system to optimize the aerodynamic efficiency and flight endurance of a lightweight aircraft. Characterized by a 770 kg payload capacity and a maximum speed of 425 km/h, the proposed vehicle underwent a rigorous development process involving aerodynamic analysis, structural configuration design, Computational Fluid Dynamics (CFD) simulations, and validation. The airframe leverages high-strength, lightweight materials specifically carbon fiber and aluminum integrated with a jet propulsion layout to reduce energy consumption. Numerical simulations demonstrate that the proposed flap configuration enhances flight endurance by approximately 36% over conventional designs. This framework exhibits strong potential for emergency response applications, including ambulatory and rescue operations, by mitigating traffic-induced delays. This study contributes directly to the advancement of energy-efficient jet engine technology and next-generation aerospace transportation systems in Malaysia.
The increasing demand for long-endurance unmanned aerial vehicles (UAVs) in environmental monitoring, precision agriculture, infrastructure inspection, surveillance, and disaster response has accelerated research into renewable-energy-powered flight systems. Conventional battery-powered UAVs are constrained by the limited specific energy of electrochemical storage systems, making aerodynamic efficiency a critical consideration in the design of solar-powered aircraft. This study presents the conceptual aerodynamic design and performance evaluation of a medium-scale solar-powered UAV using an integrated computational methodology based on XFOIL, XFLR5, and MATLAB. Three low-Reynolds-number airfoils (SD7037, MH32, and S1223) were evaluated at a Reynolds number of 3.0 × 10⁵ to identify the most suitable airfoil for extended-endurance operation. MATLAB was employed to automate the import, post-processing, visualization, and comparative analysis of aerodynamic polar data generated by XFLR5. The resulting aerodynamic characteristics were subsequently used for aircraft sizing and propulsion system selection. Results indicate that the SD7037 airfoil provided the best overall aerodynamic performance, achieving a maximum lift coefficient (CL,max) of 1.273, a minimum drag coefficient (CD,min) of 0.00704, and a maximum lift-to-drag ratio (L/Dmax) of 86.07. Based on these characteristics, a conceptual UAV with a maximum take-off mass of 25 kg and a cruise speed of 18 m/s was developed. Preliminary sizing yielded a wing area of 1.46 m², a wingspan of 3.82 m, and an aspect ratio of 10. The propulsion system consisted of an 800 W brushless DC outrunner motor, a 60 A electronic speed controller, and a 22.2 V lithium-polymer battery, providing sufficient power for take-off, climb, and cruise operations. Comparison with representative solar-powered UAV platforms demonstrated that the proposed design achieves a practical balance between aerodynamic efficiency, propulsion performance, and operational flexibility. The integrated methodology provides a reproducible conceptual design framework for future development and experimental validation of energy-efficient solar-powered UAVs.
Ibe Tochukwu C., Victor Oluikpe, Emmanuel Nnali-Uroh et al.· International journal of res...· 0 citations
Global standards for vehicle energy consumption and emissions are becoming increasingly strict. Aerodynamic optimisation has become a key technology to improve fuel efficiency, extend the driving range of electric vehicles and enhance vehicle driving stability. Data shows that every 10% reduction in aerodynamic drag coefficient can increase the fuel economy of passenger cars by 3%–5% and the driving range of pure electric vehicles by 3%–8% under high-speed cruise conditions. Aerodynamic parts such as front bumpers, side skirts, rear wings and diffusers are core components to adjust the airflow field. Passive aerodynamic parts have been widely mass-produced and applied, while active aerodynamic systems have become a popular research topic with the electrification and intelligent development of automobiles. Computational Fluid Dynamics simulation and wind tunnel tests provide support for refined component design. Current related research still has many unsolved problems, including unclear coupling mechanisms between different components, obvious conflicts between various design schemes, insufficient verification under complex working conditions, and large adaptation differences among different vehicle platforms.
With the strategic expansion of low-altitude economies, there is a growing demand for unmanned aerial vehicles (UAVs) with enhanced structural reliability and performance. This study investigates the integrated design and precision manufacturing of a heavy-lift quadrotor UAV, focusing on developing a system capable of sustaining substantial payloads. The UAV features an innovative locking mechanism at the base of its arms, which facilitates easy disassembly—this design simplifies maintenance while improving operational flexibility. Structural integrity was evaluated using the Static Structural module in Ansys Workbench under three operational conditions: no-load, full-load, and extreme-load. Results demonstrate that the airframe meets strength requirements under all conditions, though localized nonlinear deformations were observed in the arms under extreme loads. In response to these findings, the Response Surface Optimization methodology was systematically applied to refine the UAV arm’s design parameters, with the dual goals of minimizing structural mass and reducing displacement. Experimental results show that under the most demanding operating condition, the maximum displacement was reduced by 43.6% compared to the pre-optimization state, while the arm’s weight was reduced by 20.2%. These findings provide critical insights for advancing UAV design, particularly in agricultural and logistics applications that require high payload capacity and robustness.
Kang-Hui Huang, Guiying Li, Zhigang Yu et al.· SAE technical paper series· 0 citations
Aviation decarbonization is one of the greatest challenges in the pursuit of sustainable mobility. While incremental improvements in aerodynamics, structures, and propulsion have led to sensible efficiency gains over the last years, the transition toward zero emission aircraft configurations requested by international guidelines needs disruptive technologies. Liquid hydrogen propulsion systems coupled with fuel cells are one of the most promising solutions to be investigated, since they offer high energy density, clean exhaust, and compatibility with regional aircraft missions. This study presents a novel configuration for a regional aircraft propelled by liquid hydrogen and fuel cells, based on conceptual design. The proposed configuration is a high-wing aircraft with T-tail. Unlike kerosene, liquid hydrogen requires specialized tanks and insulation, which significantly influence aircraft geometry and weight distribution. To address these challenges, the proposed configuration adopts a fuselage integrated cryogenic tank system installed in the aircraft rear cone, to minimize aerodynamic penalties while ensuring safety and operational feasibility. The fuel cell system is distributed to optimize redundancy and thermal management, enabling efficient power delivery to electric propulsors. The study contributes to the growing body of literature on hydrogen aviation by providing a system level configuration tailored to regional aircraft, a segment particularly suited for early adoption of hydrogen technologies due to shorter ranges and frequent operations. The findings underline the technical feasibility of liquid hydrogen–fuel cell systems, offering insights for future certification frameworks, infrastructure development, and industrial implementation. In conclusion, this work presents a feasible configuration of a novel green regional aircraft powered by liquid hydrogen and fuel cells. The results provide a foundation for further experimental validation and pave the way for the next generation of environmentally responsible regional aircraft.
Diego Giuseppe Romano, M. Barbarino, G. Fasulo et al.· Engineering Modelling, Analy...· 0 citations
The ongoing transition toward sustainable aviation has accelerated research efforts focused on hybrid-electric and fully electric aircraft concepts. While significant advances have been achieved in electric propulsion technologies, the integration of energy storage systems within conventional aircraft platforms remains a major engineering challenge due to their impact on aerodynamic performance, mass distribution, stability characteristics, and structural loading conditions. The present work investigates the aerodynamic and flight dynamic characteristics of a modified general aviation aircraft intended as a demonstrator platform for future electric propulsion integration. A representative low-wing general aviation aircraft was selected as the baseline configuration and subsequently modified through the incorporation of a ventral energy-storage container designed to accommodate battery systems. Aerodynamic analyses were conducted using the USAF Digital DATCOM methodology under representative cruise conditions. Lift, drag, and pitching moment coefficients were evaluated over a broad angle-of-attack range, while static and dynamic stability derivatives were determined to assess longitudinal and lateral-directional stability characteristics. A nonlinear six-degree-of-freedom flight dynamics model was subsequently developed to investigate aircraft responses to control surface and propulsion commands. Numerical simulations involving aileron, elevator, rudder, and differential propulsion inputs were performed in order to evaluate controllability, stability margins, and dynamic coupling effects. The obtained results demonstrate that the modified configuration preserves satisfactory aerodynamic efficiency and dynamic stability while exhibiting only a moderate increase in drag associated with the external energy-storage system. The investigated configuration therefore represents a viable candidate for future studies involving hybrid-electric and fully electric propulsion architectures. The present work establishes a preliminary framework for multidisciplinary investigations combining aerodynamics, structures, flight mechanics, and propulsion system integration.
Octavian-Mircea Crisan, Alexandru Pasula· Romanian Journal of Technica...· 0 citations
Unmanned aerial vehicles (UAVs) increasingly demand higher flight speeds, longer endurance, improved payload capacity, and greater operational flexibility across a wide range of applications. While battery-electric propulsion systems dominate small UAV platforms, their limited energy density significantly constrains range and mission duration. Consequently, turbine-based propulsion systems, including micro turbojets, turboprops, turboshafts, and hybrid-electric gas turbine architectures, are attracting growing attention as alternatives for advanced UAV operations. Unlike previous reviews that primarily focus on propulsion technologies or individual subsystem performance, this review provides an integrated assessment of the multidisciplinary challenges associated with turbine-powered UAVs, encompassing thermal, structural, aerodynamic, acoustic, operational, and stealth considerations within a unified framework. The presented synthesis identifies current knowledge gaps and emerging research directions, providing a comprehensive reference for the design and development of next-generation turbine-powered unmanned aerial platforms.
Raluca Andreea Roșu, E. Prisăcariu, Oana Dumitrescu· Technologies· 0 citations