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Bibliografías temáticas / Aero-Propulsive

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Literatura académica sobre el tema "Aero-Propulsive"

Autor: Grafiati

Publicado: 7 de diciembre de 2024

Última modificación: 19 de julio de 2025

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Artículos de revistas sobre el tema "Aero-Propulsive"

1

STEPAN, Anca, Georges GHAZI, and Ruxandra Mihaela BOTEZ. "Development of an Adaptive Aero-Propulsive Performance Model in Cruise Flight – Application to the Cessna Citation X." INCAS BULLETIN 14, no. 4 (2022): 167–81. http://dx.doi.org/10.13111/2066-8201.2022.14.4.14.

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To accurately predict the amount of fuel needed by an aircraft for a given flight, a performance model must account for engine and airframe degradation. This paper presents a methodology to identify an aero-propulsive model to predict the fuel flow of an aircraft in cruise, while considering initial modeling uncertainties and performance variation over time due to degradation. Starting from performance data obtained from a Research Aircraft Flight Simulator, an initial aero-propulsive model was identified using different estimation methods. The estimation methods studied in this paper were pol

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2

Zhao, Wenyuan, Yanlai Zhang, Peng Tang, and Jianghao Wu. "The Impact of Distributed Propulsion on the Aerodynamic Characteristics of a Blended-Wing-Body Aircraft." Aerospace 9, no. 11 (2022): 704. http://dx.doi.org/10.3390/aerospace9110704.

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Motivated by outstanding aerodynamic performance and limited emissions, the blend-wing-body (BWB) aircraft equipped with a distributed propulsion (DP) system has become a possible layout for civil aircraft in the next generation. Due to the strong aero-propulsive interference (API) between the DP system and the airframe, the conventional integration of pressure and friction stress over the surface may fail to evaluate the aerodynamic power consumption of this layout. Here, the aero-propulsive integrated power balance approach is used alternatively to obtain the aerodynamic power consumption th

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3

Ma, Yiyuan, Chaofan Wang, Zhonghua Han, and Yue Wang. "Mid-fidelity aero-propulsive coupling approach for distributed propulsion aircraft." Aerospace Science and Technology 157 (February 2025): 109859. https://doi.org/10.1016/j.ast.2024.109859.

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4

Luo, Shaojun, Tian Zi Eng, Zhili Tang, Qianrong Ma, Jinyou Su, and Gabriel Bugeda. "Multidisciplinary Optimization of Aircraft Aerodynamics for Distributed Propulsion Configurations." Applied Sciences 14, no. 17 (2024): 7781. http://dx.doi.org/10.3390/app14177781.

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The combination of different aerodynamic configurations and propulsion systems, namely, aero-propulsion, affects flight performance differently. These effects are closely related to multidisciplinary collaborative aspects (aerodynamic configuration, propulsion, energy, control systems, etc.) and determine the overall energy consumption of an aircraft. The potential benefits of distributed propulsion (DP) involve propulsive efficiency, energy-saving, and emissions reduction. In particular, wake filling is maximized when the trailing edge of a blended wing body (BWB) is fully covered by propulsi

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Seitz, Arne, Anaïs Luisa Habermann, Fabian Peter, et al. "Proof of Concept Study for Fuselage Boundary Layer Ingesting Propulsion." Aerospace 8, no. 1 (2021): 16. http://dx.doi.org/10.3390/aerospace8010016.

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Key results from the EU H2020 project CENTRELINE are presented. The research activities undertaken to demonstrate the proof of concept (technology readiness level—TRL 3) for the so-called propulsive fuselage concept (PFC) for fuselage wake-filling propulsion integration are discussed. The technology application case in the wide-body market segment is motivated. The developed performance bookkeeping scheme for fuselage boundary layer ingestion (BLI) propulsion integration is reviewed. The results of the 2D aerodynamic shape optimization for the bare PFC configuration are presented. Key findings

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6

Baklacioglu, T., and M. Cavcar. "Aero-propulsive modelling for climb and descent trajectory prediction of transport aircraft using genetic algorithms." Aeronautical Journal 118, no. 1199 (2014): 65–79. http://dx.doi.org/10.1017/s0001924000008939.

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Abstract In this study, a new aero-propulsive model (APM) was derived from the flight manual data of a transport aircraft using Genetic Algorithms (GAs) to perform accurate trajectory predictions. This new GA-based APM provided several improvements to the existing models. The use of GAs enhanced the accuracy of both propulsive and aerodynamic modelling. The effect of compressible drag rise above the critical Mach number, which was not included in previous models, was considered along with the effects of compressibility and profile camber in the aerodynamic model. Consideration of the thrust de

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7

Swain, Prafulla Kumar, Ashok K. Barik, Siva Prasad Dora, and Rajeswara Resapu. "The propulsion of tandem flapping foil following fishtailed flapping trajectory." Physics of Fluids 34, no. 12 (2022): 123609. http://dx.doi.org/10.1063/5.0128223.

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It has always been a challenge to implement the natural flyer and swimmer kinematics into human-made aero/hydro vehicles for the enhancement of their performance. The propulsive performance of underwater vehicles can be enhanced by following the fishtailed kinematics. In the present study, a two-dimensional simulation has been performed on a tandem flapping foil by altering the simple flapping trajectory motion to a fishtailed trajectory by varying the Strouhal number ( St) in the range of 0.1–0.5. The effect of the inter-foil spacing and phasing between the foils on wake interaction is also i

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8

Yin, F., and A. Gangoli Rao. "Performance analysis of an aero engine with inter-stage turbine burner." Aeronautical Journal 121, no. 1245 (2017): 1605–26. http://dx.doi.org/10.1017/aer.2017.93.

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ABSTRACTThe historical trends of reduction in fuel consumption and emissions from aero engines have been mainly due to the improvement in the thermal efficiency, propulsive efficiency and combustion technology. The engine Overall Pressure Ratio (OPR) and Turbine Inlet Temperature (TIT) are being increased in the pursuit of increasing the engine thermal efficiency. However, this has an adverse effect on engine NOx emission. The current paper investigates a possible solution to overcome this problem for future generation Very High Bypass Ratio (VHBR)/Ultra High Bypass Ratio (UHBR) aero-engines i

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9

Corcione, Salvatore, Vincenzo Cusati, Danilo Ciliberti, and Fabrizio Nicolosi. "Experimental Assessment of Aero-Propulsive Effects on a Large Turboprop Aircraft with Rear-Engine Installation." Aerospace 10, no. 1 (2023): 85. http://dx.doi.org/10.3390/aerospace10010085.

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This paper deals with the estimation of propulsive effects for a three-lifting surface turboprop aircraft concept, with rear engine installation at the horizontal tail tips, conceived to carry up to 130 passengers. This work is focused on how the propulsive system affects the horizontal tailplane aerodynamics and, consequently, the aircraft’s static stability characteristics using wind tunnel tests. Both direct and indirect propulsive effects have been estimated. The former produces moments whose values depend on the distance from the aircraft’s centre of gravity to the thrust lines and propel

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10

Minucci, Marco A. S., and Leik N. Myrabo. "Phase distortion in a propulsive laser beam due to aero-optical phenomena." Journal of Propulsion and Power 6, no. 4 (1990): 416–25. http://dx.doi.org/10.2514/3.25452.

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Tesis sobre el tema "Aero-Propulsive"

1

Altamirano, George V. "Investigation of Longitudinal Aero-Propulsive Interactions of a Small Quadrotor Unmanned Aircraft System." The Ohio State University, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1607075603449697.

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2

Dosne, Cyril. "Development and implementation of adjoint formulation of explicit body-force models for aero-propulsive optimizations." Electronic Thesis or Diss., Institut polytechnique de Paris, 2024. http://www.theses.fr/2024IPPAX026.

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Dans le domaine de l’aéronautique civile, les études de plus en plus nombreuses portant sur les nouveaux systèmes moteurs, tels que les turbofans à très haut taux de dilution et les open-rotors, ainsi que sur les architectures d'intégration motrice innovantes, telles que la propulsion distribuée ou les systèmes à ingestion de couche limite, nécessitent une modélisation couplée de l’aérodynamique externe et du système propulsif, et ce dès les premiers stades de la conception. Les modèles body-force se sont avérés capables de reproduire fidèlement la majeure partie des phénomènes de couplage aér

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3

Arntz, Aurélien. "Civil aircraft aero-thermo-propulsive performance assessment by an exergy analysis of high-fidelity CFD-RANS flow solutions." Thesis, Lille 1, 2014. http://www.theses.fr/2014LIL10110/document.

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Les outils et méthodologie utilisés actuellement par les ingénieurs ne permettent pas d’évaluer efficacement l’intérêt de ces concepts innovants. Typiquement, le conventionnel partage poussée/traînée devient excessivement ambigu pour l’étude de systèmes propulsifs avec ingestion de couches limites. Par ailleurs, le management thermique devient un enjeux crucial pour les performances globales de l’appareil. Le travail a donc consisté à développer une méthodologie capable de prendre en compte ces différents aspects. Dans un premier temps, une formulation théorique basée sur la notion d’exergie a

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4

"Modeling, Analysis, and Control of a Hypersonic Vehicle With Significant Aero-Thermo-Elastic-Propulsion Interactions, and Propulsive Uncertainty." Master's thesis, 2010. http://hdl.handle.net/2286/R.I.8592.

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abstract: This thesis examines the modeling, analysis, and control system design issues for scramjet powered hypersonic vehicles. A nonlinear three degrees of freedom longitudinal model which includes aero-propulsion-elasticity effects was used for all analysis. This model is based upon classical compressible flow and Euler-Bernouli structural concepts. Higher fidelity computational fluid dynamics and finite elementmethods are needed formore precise intermediate and final evaluations. The methods presented within this thesis were shown to be useful for guiding initial control relevant design.

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Capítulos de libros sobre el tema "Aero-Propulsive"

1

Wervaecke, Christelle, Ilias Petropoulos, and Didier Bailly. "Assessment of Exergy Analysis of CFD Simulations for the Evaluation of Aero-Thermo-Propulsive Performance of Aerial Vehicles." In Computational Methods in Applied Sciences. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-57422-2_17.

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Actas de conferencias sobre el tema "Aero-Propulsive"

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Geuther, Steven, Benjamin Simmons, and Kasey Ackerman. "Overview of the Subscale RAVEN Flight Controls and Modeling Testbed." In Vertical Flight Society 80th Annual Forum & Technology Display. The Vertical Flight Society, 2024. http://dx.doi.org/10.4050/f-0080-2024-1185.

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The Research Aircraft for eVTOL Enabling TechNologies (RAVEN) Subscale Wind-Tunnel and Flight Test (SWFT) model is a subscale aircraft built for flight dynamics and controls research demonstrated in wind-tunnel and flight-test experiments. The intent of this paper is to provide a summary of past, current, and future efforts being pursued by the RAVEN-SWFT project. Initially, vehicle development guidelines were crafted by a multidisciplinary team to ensure that the RAVEN-SWFT vehicle was well suited for research in multiple areas, including aero-propulsive modeling, flight controls, and autonom

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2

Schmid, Sebastian, Muscan Karadayi, Daniel Tataru, and Jacob Cook. "Modeling, Simulation and System Identification of a Tilt-Wing Aircraft." In Vertical Flight Society 81st Annual Forum and Technology Display. The Vertical Flight Society, 2025. https://doi.org/10.4050/f-0081-2025-295.

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A simulation framework is essential for the development of a hybrid-electric tilt-wing aircraft such as Dufour Aerospace's Aero2 drone. The tilt-wing design with its complex interaction effects between the propellers and the aerodynamic surfaces presents unique modeling challenges, especially during early stages of development when only limited data is available. Furthermore, a delicate balance between accuracy and performance must be found while keeping complexity low to allow for rapid development. This paper introduces a modular design approach for a simulation framework, details the aero-p

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3

Simmons, Benjamin, Kasey Ackerman, Garrett Asper, et al. "Subscale Tiltrotor eVTOL Aircraft Dynamic Modeling and Flight Control Software Development." In Vertical Flight Society 81st Annual Forum and Technology Display. The Vertical Flight Society, 2025. https://doi.org/10.4050/f-0081-2025-161.

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This paper describes the dynamic modeling and flight control software development efforts for a subscale tiltrotor electric vertical takeoff and landing (eVTOL) aircraft built at NASA Langley Research Center. The vehicle, referred to as the Research Aircraft for eVTOL Enabling techNologies (RAVEN) SubscaleWind-Tunnel and Flight Test (SWFT) model, serves as a flight dynamics and controls research testbed to foster advances in eVTOL aircraft technology. After fabricating the vehicle, wind-tunnel testing was conducted to identify a high-fidelity aero-propulsive model for use in a flight dynamics

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4

Simmons, Benjamin, Andrew Rapsomanikis, George Jacobellis, NK Ofodile, Thomas Hamilton, and Max Ma. "Flight-Test System Identification Methodology and Hover Results for a Vectored-Thrust eVTOL Aircraft." In Vertical Flight Society 81st Annual Forum and Technology Display. The Vertical Flight Society, 2025. https://doi.org/10.4050/f-0081-2025-220.

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This paper describes an ongoing aircraft system identification effort for an industry prototype electric vertical takeoff and landing (eVTOL) vehicle. Building on previous eVTOL aircraft system identification developments in windtunnel testing and flight simulations, an approach to modeling from flight-test data is formulated for the AIBOT 500 aircraft. The full system identification process is presented, including the experiment design, flight data collection, and model identification steps. Orthogonal phase-optimized multisine programmed test inputs are integrated into the flight control sys

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5

TOWNEND, L., E. BROADBENT, J. CLARKE, et al. "Aero-propulsive effects on configuration shaping." In 3rd International Aerospace Planes Conference. American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-5064.

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6

Ahuja, Vivek, Imon Chakraborty, and Roy J. Hartfield. "Aero-Propulsive Analysis for Contemporary Conceptual Design." In AIAA Aviation 2019 Forum. American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-3019.

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7

de Vries, Reynard, Maurice Hoogreef, and Roelof Vos. "Aero-Propulsive Efficiency Requirements for Turboelectric Transport Aircraft." In AIAA Scitech 2020 Forum. American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-0502.

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8

Africawala, Jalendu, and Aleksandar Joksimovic. "Panel Method for Aero-Propulsive Design Space Exploration." In AIAA SCITECH 2024 Forum. American Institute of Aeronautics and Astronautics, 2024. http://dx.doi.org/10.2514/6.2024-0240.

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9

Kerho, Mike F. "Aero-Propulsive Coupling of an Embedded, Distributed Propulsion System." In 33rd AIAA Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-3162.

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10

Hosangadi, A., P. Cavallo, S. Arunajatesan, R. Ungewitter, and R. Lee. "Aero-propulsive jet interaction simulations using hybrid unstructured meshes." In 35th Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-2119.

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