A5060142872- Computational Fluid Dynamics and Aerodynamics
- Fluid Dynamics and Turbulent Flows
- Aerodynamics and Acoustics in Jet Flows
- Aerodynamics and Fluid Dynamics Research
- Wind and Air Flow Studies
- Advanced Aircraft Design and Technologies
- Acoustic Wave Phenomena Research
- Turbomachinery Performance and Optimization
- Plasma and Flow Control in Aerodynamics
- Gas Dynamics and Kinetic Theory
- Combustion and flame dynamics
- Lattice Boltzmann Simulation Studies
- Fluid Dynamics and Vibration Analysis
- Aerospace and Aviation Technology
- Radiative Heat Transfer Studies
- Wind Energy Research and Development
- Advanced Combustion Engine Technologies
- Aeroelasticity and Vibration Control
- Biomimetic flight and propulsion mechanisms
- Aerosol Filtration and Electrostatic Precipitation
Italian Aerospace Research Centre
2013-2025
Office National d'Études et de Recherches Aérospatiales
2024
Netherlands Leprosy Relief
2024
University of Naples Federico II
2022-2024
Piaggio Aerospace (Italy)
2017
Deutsches Zentrum für Luft- und Raumfahrt e. V. (DLR)
2012-2013
The focus of this paper is on some the activities performed by CIRA under framework HERWINGT project (Hybrid Electric Regional Wing Integration Novel Technologies) supported Clean Aviation Joint Undertaking and funded European Union. aim to design an innovative wing suitable for future hybrid electric regional aircraft (HER) that will contribute overall target reducing fuel burn, CO2, other GHG emissions improving aerodynamic efficiency weight. a high-lift system wings in form compliant...
Tip-mounted propellers can increase wing aerodynamic efficiency, and the concept is gaining appeal in context of hybrid electrical propulsion for greener aviation, as smaller lighter motors help with mitigating structural drawbacks a tip engine installation. A numerical study propeller effects on aerodynamics herein illustrated, considering different power configurations Regional Aircraft wing. drag breakdown analysis using far-field methods presented one most promising configurations,...
The design of high-lift systems represents a challenging task within the aerospace community, being multidisciplinary, multi-objective, and multipoint problem. Design, Simulation Flight Reynolds Number Testing for Advanced High-Lift Solution project, funded by European Commission under Seventh Framework Programme, aimed at improving aerodynamics developing, in coordinated approach, both efficient numerical strategies measurement techniques cryogenic conditions. Within different partners used...
This paper presents a numerical study of the acoustic shielding aeroengine noise by aircraft structure. More specifically, engines considered are contra-rotating open rotors in pusher mode which installed at rear aircraft. Several empennage designs and engine positions evaluated. An original method for calculation installation effects is presented its application to rotor propulsion demonstrated. It based on weak coupling between computational fluid dynamics, an integral Lighthill’s analogy...
This document explains in its first part the design procedure adopted to contoured sidewalls of a swept-wing airfoil section mounted wind tunnel order satisfy infinite approximation. In second part, experimental set-up is described as well results campaign. The are shown play their role properly and satisfactorily provide conditions required for subsequent investigations most important vortex receptivity mechanisms responsible excitation crossflow Tollmien-Schlichting instability modes...
Abstract Purpose This paper aims to simulate unsteady flows with surfaces in relative motion using a multi-block structured flow solver. Design/methodology/approach A procedure for simulating was developed, based upon U-RANS solver1. Meshes produced zones of the field different rotation speed are connected by sliding boundaries. The developed guarantees that flux conservation properties original scheme maintained across boundaries during at every time step. Findings solver turns out be very...
Purpose The paper aims to reduce the aerodynamic drag of a rotorcraft stabilizer in forward flight by taking into account downwash effects from main rotor wake (power-on conditions). Design/methodology/approach A shape design methodology based on numerical optimization, CAD-in-the-loop (CAD: computer-aided design) approach and high-fidelity Computational Fluid Dynamics (CFD) tools was set-up applied modify horizontal empennage configuration. This included integration both commercial in-house...
This paper deals with the computation of CROR installation effects in terms tone noise within three separated steps. The first step aims at computing aeroacoustic sources a by CFD approach, namely URANS method applied to counter-rotative propellers. second computes acoustic field radiated isolated CROR. It is based on Ffowcs-Williams and Hawkings (FW-H) surface integral uses blade pressure fluctuations computed as input data. last scattered aircraft geometry Boundary Element Method using...
View Video Presentation: https://doi.org/10.2514/6.2023-4090.vid A recently proposed far-field aerodynamic force theory based on the concepts of vortex and Lamb vector is here considered to investigate unsteady aerodynamics flapping wings. Vortical formulations in incompressible flow regime are derived, for inertial or non-inertial reference frames, a form valid both viscous inviscid flows. Then mixed inertial/non-inertial formulation, originally two-dimensional flows, extended...
The Lamb vector, cross-product of flow vorticity and velocity, is at the basis different far-field methods developed in last decades for aerodynamic force analysis decomposition, as an alternative to nowadays well-assessed thermodynamic methods. We here propose a mixed approach, where exact Lamb-vector-based formulas are used combination with thermodynamic-based calculation vector through Crocco's equation. In computational fluid dynamics, this way calculating therefore, inherits from...
Recent methods based on Lamb vector integration allow for a far-field formulation and decomposition of the whole aerodynamic force, with identification local flow structures associated force generation. Different exact Lamb-vector-based formulations were proposed in past total drag into lift-induced parasite contributions was subject very recent studies. However, inconsistencies also reported, raising questions physical role non-zero induced found two-dimensional flows. Moreover, effect...
Purpose This study aims to propose an aerodynamic force decomposition which, for the first time, allows thrust/drag bookkeeping in two-dimensional viscous and unsteady flows. Lamb vector-based far-field methods are used at scope, paper starts with extending recent steady compressible formulas regime. Design/methodology/approach Exact vortical derived considering inertial or non-inertial frames, inviscid flows, fixed moving bodies. Numerical applications a NACA0012 airfoil oscillating pure...
Two innovative, low noise propellers have been designed against a comprehensive set of requirements for next generation propeller driven regional aircraft. These designs scaled down wind tunnel testing and shown significant reduction when compared to state-of-the-art conventional design. Testing has carried out at both low-speed conditions associated with the community certification points high-speed cruise condition summary results are presented. Corrections derived align test data direct...
Recent methods based on flow vorticity and Lamb vector integration allow for a far-field formulation decomposition of the whole aerodynamic force with identification local structures associated generation. Different exact theoretically equivalent vector-based formulations were proposed in past total drag into lift-induced parasite contributions was subject very recent papers. However, different results can be obtained practise when applying selected formula to numerically computed...
Abstract The use of hydrogen as an alternative fuel in the combustion chamber aircraft turbine engine would offer a practical solution to reducing levels emissions which contribute atmospheric pollution. In recent years various designs basic system component such have been proposed being described micromix combustor. This technology requires design and development safe mechanism for avoids auto-ignition flashback permits initial balance mixing hydrogen-air mixture produce thrust from...