Raffaele Salvatore DonelliCIRA Centro Italiano Ricerche Aerospaziali | CIRA · fluidynamic laboratory
Raffaele Salvatore Donelli
PhD
About
55
Publications
11,190
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383
Citations
Citations since 2017
Introduction
Additional affiliations
July 2016 - present
Clean Sky Joint Undertaking
Position
- Seconded National Expert
Description
- Dissemination and Exploitation responsible for Clean Sky Programmes 1 and 2
August 2015 - June 2016
Position
- Head of Department
Description
- Development of the three-years CIRA program, cooperation with Regione Campania for the Memorandum of Understanding with Clean Sjy for the use of the ESIF funding. Responsible for AirTN H2020 project. Cooperation to Future Sky
September 2013 - July 2015
Clean Sky Joint Undertaking
Position
- Seconded Project Officer
Description
- Support to the Project Office coordinator of the Clean Sky Joint Undertaking. Development of the CS Managment Manual, support to the drafting of the CS2 Development Plan.
Publications
Publications (55)
A numerical procedure to improve the performances of a Reynolds-Averaged Navier-Stokes code by including an accurate
prediction of the location of the transition onset is presented. A transition prediction module is coupled with the Ansys
Fluent flow solver. The transition location is predicted by coupling numerical methods based on the solution of...
The capability for CFD prediction of hypersonic shock wave laminar boundary layer interaction was assessed for a double wedge model at Mach 7.1 in air and nitrogen at 2.1. MJ/kg and 8. MJ/kg. Simulations were performed by seven research organizations encompassing both Navier-Stokes and Direct Simulation Monte Carlo (DSMC) methods as part of the NAT...
This paper is aimed at providing the outcomes of an activity carried out inside an Italian National Program named VITAS (Vettore Innovativo per il Trasporto AeroSostenibile) [1]. The goal of the project was to design a transonic wing with an extended natural laminar region for a business jet (8–12 seats). Both experimental and numerical activities...
The objective of the present work is to improve the physical understanding of specific 3D stability and transition processes in 3D mean flow by using a full linear stability theory, based on a multiple scales method and ray theory. A full 3D test case in two different flow conditions has been investigated and compared against a classical transition...
The interactions between shock waves and boundary layer are commonplace in hypersonic aerodynamics. They represent a very challenging design issue for hypersonic vehicle. A typical example of shock wave boundary layer interaction is the flowfield past aerodynamic surfaces during control. As a consequence, such flow interaction phenomena influence b...
The interactions between shock waves and boundary layer are commonplace in hypersonic aerodynamics. They represent a very challenging design issue for hypersonic vehicle. A typical example of shock wave boundary layer interaction is the flowfield past aerodynamic surfaces during control. As a consequence, such flow interaction phenomena influence b...
The objective of the present work is to improve the physical understanding of specific 3D stability and transition processes in 3D mean flow by using a full stability theory, based on a multiple scales method and ray theory.
This paper is aimed at providing the outcomes of an activity carried out inside an Italian National Program named VITAS (Vettore Innovativo per il Trasporto AeroSostenibile). The goal of the project was to design a transonic wing with an extended natural laminar region for a business jet (8-12 seats). Both experimental and numerical activities were...
The present work describes the activities performed to predict transition location using linear stability theory in unsteady flow conditions. The paper will focus on the application of the unsteady method on an optimized rotor blade compared to its baseline.
The paper illustrates a research activity aimed at improving flow laminarity over the blades of a medium-sized helicopter rotor in forward flight conditions. A numerical optimization procedure integrating database transition prediction methods is used to extend the flow laminarity of rotor blades and post-design performance assessment is performed...
In this paper we report and discuss the results of the computational analysis of the
flowfield past a double wedge model that has been used in a test campaign performed in
the Hypervelocity Expansion Tube at the University of Illinois. Along with the center of the
model 19 coaxial thermocouple gauges at 16 different streamwise locations are mounted...
In this paper we report and discuss the results of the computational analysis of the flowfield past a double
wedgemodel that has been used in a test campaign performed in the Hypervelocity Expansion Tube (HET)
at the University of Illinois. Along with the center of the model, 19 coaxial thermocouple gauges at 16 different
streamwise locations are m...
Results of the application of a trapped vortex cell to an airfoil with the aim of improving the aerodynamic performances are presented for two complementary experiments arranged at CIRA and at Politecnico di Torino. In the CIRA experiments, PIV measurements on a simplified configuration were carried out to characterize the trapped vortical structur...
In the framework of laminar–turbulent flows, the prediction of transition is a demanding design issue. It has a major influence on friction drag, leading edge separation and boundary layer thickness, the latter impacting upon other key features such as shock– wave position and associated wave drag in transonic flows. Furthermore, thermal fluxes in...
Negli ultimi venti anni il costo dei carburanti ha subito un notevole aumento con un significativo impatto sui costi del trasporto aeronautico. Inoltre, la Comunità Europea ha lanciato una politica di salvaguardia dell’ambiente in cui viviamo introducendo severi vincoli sull’emissione di gas inquinanti, quali l’anidride carbonica e gli ossidi di az...
The results in this paper arise from an investigation into control strategies designed to trap a vortex in a cavity such that the flow remains attached with no large scale vortex shedding. Progress in this general area is required to advance the development of thick winged aircraft where, for example, such wings could be used to store more fuel. A...
A major part of the experimental work on surface dielectric barrier discharge (DBD) actuators was carried out
in flow speeds up to 30 m/s, mostly with actuators driven by AC-voltage. With increasing flow speed, however,
the actuator’s control capacity decreases because the ionic wind generated by the AC-driven DBD is up to now
limited to a few mete...
The effects of a trapped vortex cell (TVC) on the aerodynamic performance of a NACA0024 wing model were investigated experimentally
at Re=106 and 6.671056.67\times 10^{5}. The static pressure distributions around the model and the wake velocity profiles were measured to obtain lift and drag
coefficients, for both the clean airfoil and the controlle...
A transonic aerodynamic optimization problem of industrial interest may require several gen-
erations of a classical genetic algorithm, with population sizes that may demand tremendous
amounts of CPU time, because the evaluation of the objective functions requires the usage of
a full-order numerical flow solver. This work presents a different appro...
The aim of this work is the validation of a Hybrid Model able to perform,
rapidly and efficiently, an aerodynamic analisys on airfoil in compressible regime,
preserving the accuracy of a Reynolds-Average Navier-Stokes model. The final pur-
pose is to replace a Full Order Solver in an optimization tool, based on Evolutionary
Algorithm, in order to r...
The aim of this work is to present a hybrid method to solve, rapidly and efficiently,
the aerodynamic flow field around a 2-D airfoil geometry. The objective is to replace a full order
solver, such as the Reynolds Average Navier-Stokes equations solver, in an optimization tool,
based on genetic algorithm, to speed-up the procedure. For this purpose...
The present investigation has been carried out within the SUPERTRAC project funded by the European Community in the 6th Framework Programme and aimed at investigating various techniques within laminar flow technology applied to supersonic drag reduction. In particular, this work deals with natural laminar flow shape design of a supersonic high-swee...
Unpredicted boundary layer transition can impact dra matically the
stability of the vehicle, its aerodynamic co efficients and reduce the
efficiency of the thermal protection system. In this frame, ESA started
the EXPERT (Eu ropean eXPErimental Reentry Testbed) program to pro vide
and perform in-flight experiments in order to obtain aerothermodynam...
The ESA European Space Agency is currently developing the project EXPERT - Experimental Re-entry Vehicle Test-bed. The EXPERT capsule features a generic simple shape and will perform a sub-orbital ballistic hypersonic flight; with a selection of major shape parameters to avoid any surface active oxidation, degradation and flow contamination. In the...
This paper presents an attempt to control the laminar-turbulent transition on a swept wing in supersonic flow. The first part deals with the control of the transition due to crossflow (CF) instabilities present on a swept wing, by using Micron-Sized Roughness elements (MSR); the second one
is focused on the prevention of the turbulent contamination...
A wind-tunnel experiment on laminar-turbulent transition has been performed in ETW at high Reynolds number and cryogenic conditions. The studied geometry is a swept-wing configuration. The transition location was determined by means of Temperature Sensitive Paint (TSP). The experimental observations were further analysed using different transition...
Experimental results of trapping vortices on a thick airfoil by using a cavity and an inside unsteady mass flow suction have
been investigated emphasizing drawback and benefits of the use of forcing suction compared to a simple steady suction system.
The Pathfinder model was designed in the course of the TELFONA European Research Project as a calibration tool to evaluate the transonic, cryogenic ETW facility for laminar flow testing, and assess the possibility for studies of NLF or HLF wings in ETW. The Pathfinder wing is a simplified, low taper, swept wing with an optimized profile allowing al...
A transonic natural-laminar-flow wing design procedure has been set up, integrating a parametric geometry model with several analysis tools. A direct design strategy has been applied and three levels of aerodynamic analysis have been used: a full-potential method (with which to rapidly iterate to obtain the target pressure distribution), an Euler s...
With the goal of studying Natural Laminar Flow (NLF) wings for future ‘green’ transport aircraft, the aim of the European Research Project TELFONA is to develop and demonstrate the
possibility of testing full aircraft models at large Reynolds numbers in the cryogenic Wind Tunnel
ETW, with direct measurements of total drag. Two main steps were defin...
![Fig. 5: NASA modified Van Driest criterion[16]](profile/Raffaele-Donelli/publication/234056432/figure/fig3/AS:300105967128599@1448562246583/NASA-modified-Van-Driest-criterion16_Q320.jpg)
![Fig. 7: Reda's results using PANT correlation [21]](profile/Raffaele-Donelli/publication/234056432/figure/fig4/AS:300105967128600@1448562246610/Redas-results-using-PANT-correlation-21_Q320.jpg)
![Fig. 8: Range of variations of Re kkT [16]](profile/Raffaele-Donelli/publication/234056432/figure/fig5/AS:300105967128601@1448562246643/Range-of-variations-of-Re-kkT-16_Q320.jpg)
This paper describes the Design of Experiment to study the laminar-turbulence
transition phenomenon in Hypersonic regime on a 3-deg half-angle sphere-cone
model. The huge number of factors (as bluntness, distributed roughness, Mach and
Reynolds numbers, etc.), that affect the laminar-turbulent transition, makes this
phenomenon very complex and expe...
Modern aircraft lifting surfaces are designed to have high lift–to–drag ratios in order to
minimize both the emission of pollutants and the fuel burn. To achieve this aim, a central
issue is the design of thin and streamlined wings. However, the tendency to design
commercial aircraft of larger dimensions, or innovative configurations such as Blende...
Experimental results of trapping vortices on a thick airfoil by using a cavity and an inside unsteady mass flow suction have been investigated emphasizing drawback and benefits of the use of forcing suction compared to a simple steady suction system.
Laminar-turbulent transition remains a critical issue in a number of cases, among which drag reduction, performance prediction of high lift systems, improved accuracy in general CFD, or reduction of computation cycles for development of optimization tools. Transition delay remains one of the most promising technologies for reducing air transport en...
Laminar-turbulent transition is commonly recognized as an important factor in the design of re-entry vehicles. In the framework of the European project EXPERT, organized by the European Space Agency (ESA), CIRA and ONERA have worked together to design and implement on the EXPERT capsule an experiment on natural transition. The aim of the present wo...
The flow inside a vortex trapping cavity is simulated by a suite of models: point vortex, Prandtl–Batchelor flow,
and Reynolds-averaged Navier–Stokes equations. The scope is to ascertain to what extent an inviscid model can be
used to design vortex cells. It turns out that the Prandtl–Batchelor flow, with an appropriate jump in the Bernoulli
consta...
The supersonic aircraft transport is still a challenge for the aeronautical scientific community. In the recent years, several European Community funded projects have been devoted to find new engineering solutions to reduce costs and pollution impact. Indeed, at supersonic speeds the high drag amount and noise levels call for a careful design proce...
A trapped vortex device is a cavity to trap flow vortices to reduce pressure drag levels past bluff bodies and/or thick wing airfoils. Preliminary studies showed the need to apply a constant mass flow suction inside the cavity to stabilize the vortex. The aim of this work is to find the best location and the minimum suction distribution to be applied...
This paper presents an attempt to control the laminar-turbulent transition on a swept wing in supersonic flow. The first part deals with the control of the transition due to crossflow (CF) instabilities present on a swept wing, by using Micron-Sized Roughness elements (MSR); the second one is focused on the prevention of the turbulent contamination...
A wind-tunnel experiment on laminar-turbulent transition has been performed in ETW at high Reynolds number and cryogenic conditions. The studied geometry is a swept-wing configuration. The transition location was determined by means of Temperature Sensitive Paint (TSP). The experimental observations were further analysed using different transition...
Boundary-layer unsteady blowing is one of the most advanced solutions for reducing aircraft parasite drags and
flow separation at high angles of attack. It allows high lift along with low drag to be achieved and, because endurance
is one of the most important performance parameters for certain types of aircraft, such as unmanned aerial vehicles,
cl...
The present paper deals with the control of the laminar-turbulent transition on a swept wing in supersonic conditions. This study has been carried out as part of the European Project SUPERTRAC (SUPERsonic TRAnsition Control; January 2005, June 2008). Two issues have been addressed with the same model: the first one is the control of the transition...
One of the challenges of modern numerical aerodynamics is the design of swept wing shapes with a large extension of laminar flow in their working conditions. These types of wings have a tremendous performance advantage, in terms of viscous drag force, with respect to traditional turbulent wings. On the other side, their design, manufacturing proces...
In the present investigation Digital Particle Image Velocimetry (DPIV) has been applied to the study of
a flat plate turbulent boundary layer interacting with a 2D synthetic jet. Changes in the mean flow field have been analyzed for different yaw angles of the synthetic jet slit and for different actuation frequencies. A particular attention has be...
Laminar-turbulent transition is commonly recognized as an important factor in the
design of re-entry vehicles. In the framework of the European project EXPERT, organized
by the European Space Agency (ESA), CIRA, ONERA and VKI are working together to
design and implement on the EXPERT capsule an experiment on induced transition. The
aim of the prese...
Summary Laminar flow control of aircraft gains importance due to both economic and environmental aspects. In this paper several solutions for passive devices and one proposal for an active device for laminar flow control on swept wings are presented. The passive devices concern the anti contamination devices (ACD) which are capable to stop the span...
Questions
Question (1)
I have found a dissemination activity with the title " Fire suppression systems in aircraft: Their past, present & future" and authors Guillermo Fernandez-Cerezo, Claire M. Benson, Paul G Holborn, David Mba. I am the D&E and Open Data Manager of Clean Sky and I have to assess the D&E activity. Can you provide me mor einformation on what it is this activity? It seems a paper but since are mentioned pages from Fire Investigation, 1 (3). pp. 34-41 but I need to have these info. My clean Sky mail is: Raffaele.donelli@cleansky.eu or you can submit the paper to the Clean Sky Project Officer that is following your project, but please I need asap of these info. Thank you Raffaele S. Donelli
Projects
Projects (7)
EU research project 6th Framework Program, Aeronautics and Space, Specific Target Research Project “VCELL” for studying new flow control devices based on innovative geometries.
VortexCell2050 delivered a new technological platform combining the two cuttingedge technologies, the trapped-vortex and the active flow control. The project outcomes serve the designers of the next-generation thick-wing aircraft. Thickwing, or blended wing-body, aircraft are identified as prospective for development over the next 50 years.
