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Relevant bibliographies by topics / Aerodynamic stand

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Academic literature on the topic 'Aerodynamic stand'

Author: Grafiati

Published: 28 May 2022

Last updated: 31 July 2025

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Journal articles on the topic "Aerodynamic stand"

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KRIVOSHEIN, M. A., K. D. SMIRNOV, and K. V. MESHKO. "DETERMINATION AERODYNAMIC CHARACTERISTICS OF ELEMENTS OF BUILDING VENTILATION SYSTEMS IN LABORATORY CONDITIONS." Actual Issues Of Energy 3, no. 1 (2021): 049–53. http://dx.doi.org/10.25206/2686-6935-2021-3-1-49-53.

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The article presents the layout and appearance of the stand, developed to determine the aerodynamic characteristics of the elements of ventilation systems. The technique of determining the aerodynamic characteristics of ventilation elements using the developed stand is considered. The results of tests of a check valve used in natural ventilation systems of buildings are presented. The obtained characteristic of the check valve is proposed to be used in calculating and predicting the operation of ventilation systems in buildings in which the check valves under consideration will be installed

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Yates, E. Carson. "Integral Equation Methods for Linear and Nonlinear Aerodynamics." Applied Mechanics Reviews 44, no. 11S (1991): S285—S294. http://dx.doi.org/10.1115/1.3121367.

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This paper reviews the NASA Langley Research Center program for development of integral-equation aerodynamic methods with emphasis on application in computed-aided multidisciplinary design processes as well as in aerodynamic design and stand-alone analysis. The accomplishments, status, and outlook of the program are discussed in order to highlight the scope, generality, versatility, and attractive features of this methodology, especially for application to nonlinear problems.

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An, Xiao Wei, Shu Ping Zheng, and Yu Jie Ji. "Study on Aerodynamic Properties of Impact Plate." Applied Mechanics and Materials 157-158 (February 2012): 970–75. http://dx.doi.org/10.4028/www.scientific.net/amm.157-158.970.

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An aero dynamical finite element model on rotary hammering test stand was established in this paper. The external flow field of the model was analyzed by CFD module of ANASYS-FLOTRAN. The distribution of flow velocity and that of flow pressure were obtained, which were analyzed to provide theoretical references for optimum design of impact plate.

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Panayotov, Filip, Ivan Dobrev, Fawaz Massouh, and Michael Todorov. "Experimental study of a helicopter rotor model in hover." MATEC Web of Conferences 234 (2018): 01002. http://dx.doi.org/10.1051/matecconf/201823401002.

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This paper presents the results from an experimental study of the aerodynamic performance and efficiency of a model helicopter rotor in steady hover at Reynolds numbers below 70000. Results are shown for a two-, three- and four-bladed rotor configuration for various pitch angles and speeds of rotation. The influence of the rotor solidity on the aerodynamic efficiency in terms of the Figure of Merit is highlighted. The profile drag component is evaluated as a function of the Reynolds number. The internal friction losses of the test stand are estimated and taken into account in all measurements.

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Batuhtin, Andrej, Marina Baranovskaja, Sergey Batuhtin, and Irina Batukhtina. "Aerodynamic parameters features of air flows in ventilation pipes of underground mining workings." Sustainable Development of Mountain Territories 17, no. 1 (2025): 402–13. https://doi.org/10.21177/1998-4502-2025-17-1-402-413.

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Introduction. The article discusses the features of gas flow in T-shaped pipeline connections, which are widely used in many industries and farms, such as underground mining, energy, water supply, and pneumatic transmission systems. A study of the aerodynamic characteristics of air flows in channels of different diameters connected by a tee has been conducted, and the problems and prospects of improving the efficiency of ventilation equipment in mining enterprises by optimizing air supply processes in the design process, taking into account flow aerodynamics, have been analyzed. The purpose of

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Osintcev, K. V., and S. I. Kuskarbekova. "Development of an automated control system for an educational laboratory stand." Bulletin of the South Ural State University. Ser. Computer Technologies, Automatic Control & Radioelectronics 22, no. 3 (2022): 141–50. http://dx.doi.org/10.14529/ctcr220313.

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The training laboratory stand was created to simulate the operation of a direct-flow boiler, in order to study the hydraulic and thermophysical processes occurring in such devices. Having studied the hydrodynamics of the coolant in a cylindrical composite coil, it is possible to influence the steam capacity of the boiler, improve its energy efficiency. For educational purposes, the student can study the flow modes of liquid and air, learn how to control electrical equipment, master the operation of shut-off valves and parting devices for measuring flow, temperature and pressure. The purpose of

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Bozheeva, D. M., D. A. Dekterev, Ar A. Dekterev, A. A. Dekterev, and D. V. Platonov. "Aerodynamics of airfoil moving along a circular trajectory." Journal of Physics: Conference Series 2119, no. 1 (2021): 012154. http://dx.doi.org/10.1088/1742-6596/2119/1/012154.

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Abstract An experimental and computational study of the NACA0016 airfoil has been carried out for two cases: a stationary airfoil in an incoming flow on an aerodynamic stand and an airfoil moving along a circular trajectory in a stationary flow in a hydrodynamic stand. The Reynolds number for both cases was 60000. A qualitative comparison of the velocity fields for the cases with smooth airflow and boundary layer separation was carried out. It is shown that the used calculation methods describe the task under study with sufficient quality.

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Vavilov, I. S., P. S. Yachmenev, V. V. Fedyanin, et al. "Two-gaps microwave ion engine and its study by aerodynamic method." Omsk Scientific Bulletin. Series Aviation-Rocket and Power Engineering 6, no. 1 (2022): 109–17. http://dx.doi.org/10.25206/2588-0373-2022-6-1-109-117.

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The article contains the authors’ research in the field of jet propulsion systems with low energy consumption of small spacecraft of the class of nanosatellites. The paper presents a microwave ion engine with double acceleration of ionized gas in the gaps formed by the end surfaces of cylindrical resonators. The results of an experimental study of the pressure force of a jet set of ionized gas by the aerodynamic double angle method are presented. A stand for determining the power parameters of week plasmajet is presented. The design of the prototype is presented. The total energy consumption o

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Safonov, Vladimir, Eduard Zhalnin, Marina Lapa, and Dmitry Bordan. "Use of vortex flows for aerodynamic threshing of agricultural crops." E3S Web of Conferences 126 (2019): 00004. http://dx.doi.org/10.1051/e3sconf/201912600004.

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The presence of self-oscillations in the vortex tube allowed threshing of various agricultural crops in it, such as rice, corn, wheat, oats, etc. For aerodynamic threshing of agricultural crops, the following installations were used: for threshing of selection samples, a tube 50 mm in diameter; for threshing corn cobs with a pipe with a diameter of 300 mm, 500 mm and a diameter of 1000 mm; threshing unit (pipes with a diameter of 1.2 ÷ 2 m), an unconventional vortex aerodynamic stand for threshing crops. According to the results of experiments, the threshing parameters are presented.

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Berra, Andrea, Miguel Ángel Trujillo Soto, and Guillermo Heredia. "Aerodynamic Interaction Minimization in Coaxial Multirotors via Optimized Control Allocation." Drones 8, no. 9 (2024): 446. http://dx.doi.org/10.3390/drones8090446.

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Coaxial multirotors, characterized by overlapping rotors, represent a common solution to increasing payload capacity while maintaining a compact platform size. However, the overlap between motors generates airflow disturbances that, if not taken into account properly, may decrease the system’s overall performance. In this paper, aerodynamic interactions for coaxial multirotors are analyzed and characterized. Two rotor models are introduced, which account for the aerodynamic interaction between the upper and the lower rotor. Each model is accompanied by its corresponding mixer design and analyz

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Dissertations / Theses on the topic "Aerodynamic stand"

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Fink, Jason J. "Aeromobile regenerative supercirculation test stand (ARSTS)." Ohio : Ohio University, 2004. http://www.ohiolink.edu/etd/view.cgi?ohiou1176147288.

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Калинкевич, Николай Васильевич, Микола Васильович Калінкевич, Mykola Vasylovych Kalinkevych та Н. А. Лазоренко. "Расчет и проектирование аэродинамического стенда". Thesis, Сумский государственный университет, 2017. http://essuir.sumdu.edu.ua/handle/123456789/62593.

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В данном проекте рассмотрены основные подходы и методы расчета аэродинамического стенда. Расчет и проектирование центробежных компрессоров, а также их дальнейшее совершенствование по-прежнему базируется на экспериментальных исследованиях ступеней и секций центробежных компрессоров и их элементов.

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Thakur, Ruchi. "Experimental Analysis of Shock Stand off Distance over Spherical Bodies in Hypersonic Flows." Thesis, 2015. http://etd.iisc.ac.in/handle/2005/3848.

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One of the characteristics of the high speed ows over blunt bodies is the detached shock formed in front of the body. The distance of the shock from the stagnation point measured along the stagnation streamline is termed as the shock stand o distance or the shock detachment distance. It is one of the most basic parameters in such ows. The need to know the shock stand o distance arises due to the high temperatures faced in these cases. The biggest challenge faced in high enthalpy ows is the high amounts of heat transfer to the body. The position of the shock is relevant in knowing the temperatu

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Thakur, Ruchi. "Experimental Analysis of Shock Stand off Distance over Spherical Bodies in Hypersonic Flows." Thesis, 2015. http://etd.iisc.ernet.in/2005/3848.

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One of the characteristics of the high speed ows over blunt bodies is the detached shock formed in front of the body. The distance of the shock from the stagnation point measured along the stagnation streamline is termed as the shock stand o distance or the shock detachment distance. It is one of the most basic parameters in such ows. The need to know the shock stand o distance arises due to the high temperatures faced in these cases. The biggest challenge faced in high enthalpy ows is the high amounts of heat transfer to the body. The position of the shock is relevant in knowing the temperatu

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Books on the topic "Aerodynamic stand"

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Kitaplioglu, Cahit. Analysis of small-scale rotor hover performance data. National Aeronautics and Space Administration, Ames Research Center, 1990.

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Analysis of small-scale rotor hover performance data. National Aeronautics and Space Administration, Ames Research Center, 1990.

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Analysis of small-scale rotor hover performance data. National Aeronautics and Space Administration, Ames Research Center, 1990.

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Book chapters on the topic "Aerodynamic stand"

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Kostyukov, V. A., A. M. Mayevsky, and N. K. Poluyanovich. "Development of a Software and Hardware Stand for Aerodynamic and Electromechanical Characteristics Calculation of a Vortex Type Wind-Driven Power Plant." In Society 5.0: Human-Centered Society Challenges and Solutions. Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-95112-2_19.

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Watkins, Tyler, Jesse Redford, Franklin Green, Jerry Dahlberg, Peter Tkacik, and Russell Keanini. "Hypersonic Flow over Closed and Open Nose Missile Bodies: Raw and SVD-Enhanced Schlieren Imaging, Numerical Modeling, and Physical Analysis." In Boundary Layer Flows - Modelling, Computation, and Applications of Laminar, Turbulent Incompressible and Compressible Flows [Working Title]. IntechOpen, 2022. http://dx.doi.org/10.5772/intechopen.105617.

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Understanding and mitigating against high heat loads at leading and blunt aerodynamic surfaces during hypersonic flight represents an ongoing technological challenge. Recent work has shown that the commercial software package, STAR CCM+, can provide reliable predictions of hypersonic aerothermodynamic flow and heating, under a wide range of complex, but common conditions. This chapter presents a preliminary experimental and numerical investigation of hypersonic flow over closed- and open-nose missile bodies, where the latter have been proposed as a means of reducing leading edge heat transfer.

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Morowitz, Harold J. "The Afternoon Session." In Entropy and the Magic Flute. Oxford University PressNew York, NY, 1993. http://dx.doi.org/10.1093/oso/9780195081992.003.0038.

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Abstract LUNCH Is OVER. We find our way back to the lecture hall and, in a certain disorder, wend our way back to our seats. Left over from the morning are the notes, the material on the blackboard, the slides in the projector, and the stale air. It must be difficult to build a large room with no aerodynamic mobility so that all exchange is by diffusion only. However, the architect of this hall has succeeded remarkably well in designing a convection-free, crosscurrent-free structure that maintains a continuous thermal inversion. In constant collision with the ceiling and walls are all the mole

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Chitra, P., and A. Saleem Raja. "Enhancing Aerospace Engineering Through Synergies of AI and Blockchain Technologies." In AI and Blockchain Optimization Techniques in Aerospace Engineering. IGI Global, 2024. http://dx.doi.org/10.4018/979-8-3693-1491-3.ch005.

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The aerospace industry stands at the forefront of technological advancements, seeking innovative solutions to enhance safety, efficiency, and sustainability. This chapter explores the synergies between artificial intelligence (AI) and blockchain technologies, presenting optimization techniques that promise transformative impacts on aerospace engineering practices. The integration of AI algorithms in aerospace operations spans autonomous systems, predictive maintenance, design optimization, and crew support. Autonomous navigation and control benefit from AI's adaptive decision-making, while pre

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Elakya, R., R. Thanga Selvi, T. Manoranjitham, and S. Shanthana. "Synergizing AI and Blockchain." In AI and Blockchain Optimization Techniques in Aerospace Engineering. IGI Global, 2024. http://dx.doi.org/10.4018/979-8-3693-1491-3.ch010.

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The aerospace industry stands on the brink of transformative advancements with the convergence of artificial intelligence (AI) and blockchain technologies. The chapter commences by highlighting the imperative role of AI and blockchain in the aerospace sector. Subsequently, the chapter delves into the distinct applications of AI within aerospace engineering. Autonomous systems, empowered by AI, are explored for their influence on unmanned aerial vehicles (UAVs), spacecraft navigation, and decision-making. The integration of AI-driven predictive maintenance algorithms emerges as a pivotal strate

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Mateja, Krzysztof, and Wojciech Skarka. "Simulation Model of Solar Powered UAV." In Advances in Transdisciplinary Engineering. IOS Press, 2022. http://dx.doi.org/10.3233/atde220674.

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This article presents the results of work of power supply system of an unmanned aerial vehicle (UAV) powered by solar cells. The goal of work was to develop simulation model which allow us to calculate the flight time for the input assumptions. The UAV power supply system main elements are photovoltaic cells and batteries. In the model we also included energy consumption devices (electric motors, servos, steering and measuring devices) and electricity converters. Adapting the model to the proposed technical system required detailed identification tests of the components used in the project. Fo

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Conference papers on the topic "Aerodynamic stand"

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Heckmeier, Florian M., Jan-Arun Faust, Jonathan Pflüger, Ulrich Hartmann, and Marco Stuhlpfarrer. "Aerodynamic Analysis Framework for eVTOL Aircraft at ERC." In Vertical Flight Society 81st Annual Forum and Technology Display. The Vertical Flight Society, 2025. https://doi.org/10.4050/f-0081-2025-212.

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This paper presents an overview of the comprehensive aerodynamic framework developed at ERC for the analysis and simulation of electric vertical takeoff and landing (eVTOL) aircraft. Addressing the challenges inherent to distributed propulsion architectures and the complex transition between hover and forward flight, the methodology integrates multi-fidelity simulation tools ranging from analytical models and low-fidelity simulation to fully-resolved transient CFD. The framework addresses all phases of aircraft design and validation, and includes dedicated insight into aeroacoustics, aeroelast

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Coleman, David, Joseph Heimerl, Atanu Halder, Eric Greenwood, and Moble Benedict. "On the Design and Testing of a Full-Scale Quiet and Efficient eVTOL Propeller." In Vertical Flight Society 81st Annual Forum and Technology Display. The Vertical Flight Society, 2025. https://doi.org/10.4050/f-0081-2025-139.

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This paper describes the design, development, and testing of a full-scale eVTOL propulsor optimized for quiet and efficient operation. To design the propulsor, a design tool was developed for predicting the aerodynamic and acoustic performance of eVTOL propellers and rotors. The design tool consists of an aerodynamic prediction code, AMP (Aerodynamic Modeling of Propulsor), and an acoustics prediction code, OpenCOPTER, coupled with an acoustics propogator, PSU-WOPWOP, which can receive inputs from either an acoustic solver or high-fidelity CFD. The tool was used to design a coaxial eVTOL propu

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Bi, Naipei, Anish Sydney, Kevin Kimmel, and David Haas. "Experimental Investigation of Fan Aerodynamic Performance for Fan-In-Wing Applications." In Vertical Flight Society 71st Annual Forum & Technology Display. The Vertical Flight Society, 2015. http://dx.doi.org/10.4050/f-0071-2015-10505.

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The aerodynamic performance of a series of generic isolated fan configurations are experimentally investigated in the Naval Surface Warfare Center Carderock Division (NSWCCD) 8-by-10 foot Subsonic Wind Tunnel. The goal of this work is to develop a benchmark dataset that can enhance the fundamental understanding of the fluid dynamic interactions between a generic fan and wing for Fan-In-Wing (FIW) and embedded fan configurations These configurations have significant applications for aircraft as well as underwater systems. The research is performed in three phases; isolated fans in hover flow co

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Tinney, Charles, Bryson Hill, John Valdez, Jayant Sirohi, and Christopher Cameron. "Drone Acoustics at Static Thrust Conditions." In Vertical Flight Society 73rd Annual Forum & Technology Display. The Vertical Flight Society, 2017. http://dx.doi.org/10.4050/f-0073-2017-12288.

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Multirotor drones are becoming increasingly popular in both the civilian and military sectors of our society. These compact gadgets come in a variety of sizes with the smallest ones measuring less than two inches in diameter, while larger ones can be in excess of five feet. Surprisingly, very little is known about their acoustical footprint, which is becoming a topic of broad importance given that these vehicles most often operate in populated areas. Thus, the objective of this paper is to provide a first principles understanding of the acoustical characteristics of hovering drones. To accompl

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Yang, Xuan, Aswathi Sudhir, Atanu Halder, and Moble Benedict. "Aeroelastic Analysis for Highly Flexible Flapping Wing in Hover." In Vertical Flight Society 73rd Annual Forum & Technology Display. The Vertical Flight Society, 2017. http://dx.doi.org/10.4050/f-0073-2017-12114.

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Aeromechanics of a flexible flapping wing is a complex nonlinear fluid-structure interaction problem and therefore, cannot be analyzed using conventional linear aeroelasticity methods. This paper presents a stand-alone coupled aeroelastic framework for highly flexible flapping wings in hover for Micro Aerial Vehicle (MAVs) application. A realistic hover-capable flapping-wing MAV utilizes highly flexible wings operating at high frequencies/amplitudes, which causes extreme wing deflections and highly unsteady, vortical flows. The strong fluid-structure coupling and the complicated flow physics m

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Pollack, Michael, John Steward, Jacob Neiswonger, Michael Gerardo, Vera Klimchenko, and Marc Regan. "CH-53K Aircraft Performance Verification." In Vertical Flight Society 80th Annual Forum & Technology Display. The Vertical Flight Society, 2024. http://dx.doi.org/10.4050/f-0080-2024-1366.

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The CH-53K® King Stallion™ is the most advanced heavy lift helicopter developed by Sikorsky, a Lockheed Martin Company, to address the requirements of the United States Marine Corps. The aircraft was designed to support missions with a maximum design gross weight of 88,000 lbs and can carry external loads up to 36,000 lb. Performance flight tests for the CH-53K® have been completed as part of its System Design and Development (SDD) phase. Tethered hover and level forward flight performance measurements have been acquired that are used as a basis for Naval Air Training and Operating Procedures

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Lorber, Peter, Brian Wallace, and Mark Scott. "Internal and Blade Surface Pressure Measurements of Centrifugal Flow Control on a Large Scale Rotor." In Vertical Flight Society 73rd Annual Forum & Technology Display. The Vertical Flight Society, 2017. http://dx.doi.org/10.4050/f-0073-2017-11996.

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A large scale rotor test has been performed to evaluate concepts for improving the high thrust and high speed capabilities of an edgewise single rotor helicopter. The primary approach was to alleviate dynamic stall using centrifugally pumped steady blowing, referred to as Retreating Side Blowing (RSB). This concept was studied earlier for an airfoil with a flow control slot able to generate momentum coefficients of 0.03 to 0.05 using computational simulation and experiment. The current experiment uses a 28 ft diameter rotor having an inlet at the blade root, a hollow spar, and a series of flow

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Aggarwal, Diksha, Rahul Ramanujam, Abhishek A., and Debopam Das. "Performance Measurement of a Novel Dissimilar Coaxial Rotor System." In Vertical Flight Society 80th Annual Forum & Technology Display. The Vertical Flight Society, 2024. http://dx.doi.org/10.4050/f-0074-2018-12715.

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This paper presents the preliminary results from the experimental study of the aerodynamic characterization of a novel dissimilar coaxial rotor concept with reduced rotor-rotor interaction. The performance of dissimilar coaxial rotor concept is compared with existing rotor configurations such as conventional single main-rotor tail-rotor and regular coaxial rotor. The performance measurement is carried out using a small scale coaxial hover test stand facility setup for this purpose. The hover performance of different rotor concepts namely conventional, regular coaxial and dissimilar coaxial rot

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Karli, Geoffrey, Sihong Yan, and Jose Palacios. "Full-Scale EVTOL Rotor Icing Wind Tunnel Testing." In Vertical Flight Society 80th Annual Forum & Technology Display. The Vertical Flight Society, 2024. http://dx.doi.org/10.4050/f-0080-2024-0034.

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In recent years, the electrically powered Urban Air Mobility (UAM) market has witnessed significant growth, fueled by advances in electric motor and high-power-density lithium battery technologies. This surge of interest has prompted an exploration into the design and functionality of electric vertical take-off and landing (eVTOL) vehicles, particularly those with multi-tilt-rotor configurations. These eVTOL vehicles, capable of operating at higher RPMs than traditional helicopters, face unique challenges, especially under adverse environmental conditions such as icing. Aircraft airframe icing

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Jung, Yong, Bharath Govindarajan, and James Baeder. "A Hamiltonian-Strand Approach for Aerodynamic Flows Using Overset and Hybrid Meshes." In Vertical Flight Society 72nd Annual Forum & Technology Display. The Vertical Flight Society, 2016. http://dx.doi.org/10.4050/f-0072-2016-11387.

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A solution framework using Hamiltonian paths and strand grids (HAMSTR) is presented for three-dimensional flows on overset and hybrid meshes. The methodology creates a volume mesh starting from an unstructured surface mesh that can be comprised of mixed triangular-quadrilateral elements. "Linelets" through the meshes are found in a robust manner and the solver uses line-implicit schemes and high-order reconstruction schemes along these linelets, similar to a structured solver. The mesh system is also extended to utilize overset meshes. This overset technique allows for multiple mesh systems, w

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