A5015655757- Gas Dynamics and Kinetic Theory
- Computational Fluid Dynamics and Aerodynamics
- Rocket and propulsion systems research
- Plasma and Flow Control in Aerodynamics
- Fluid Dynamics and Turbulent Flows
- Advanced Aircraft Design and Technologies
- Energetic Materials and Combustion
- Ionosphere and magnetosphere dynamics
- Particle Dynamics in Fluid Flows
- Nuclear reactor physics and engineering
- Radiative Heat Transfer Studies
- Heat transfer and supercritical fluids
- Aerospace Engineering and Control Systems
- Combustion and flame dynamics
- Advanced Combustion Engine Technologies
- Aerodynamics and Fluid Dynamics Research
- Radiation Effects in Electronics
- Magnetic confinement fusion research
- Hydraulic and Pneumatic Systems
- Aerodynamics and Acoustics in Jet Flows
- Spacecraft Dynamics and Control
- Fusion materials and technologies
- Spacecraft and Cryogenic Technologies
- Plasma Applications and Diagnostics
- Meteorological Phenomena and Simulations
Italian Aerospace Research Centre
2012-2024
Istituto Nazionale di Fisica Nucleare
2023
Bentham Science Publishers (United Arab Emirates)
2014
Bentham Science Publishers (China)
2014
Space (Italy)
2012
Covers advancements in spacecraft and tactical strategic missile systems, including subsystem design application, mission analysis, materials structures, developments space sciences, processing manufacturing, operations, applications of technologies to other fields.
Supersonic plasma jet targets can improve the present knowledge on low energy nuclear reaction cross sections allowing to study electron screening effects. They could also be employed both in preliminary tests of space vehicles thermal protection systems and validation computational fluid dynamics (CFD) evaluation hot exotic gases. This common interest between astrophysics research led a joint effort European Recoil Separator for Nuclear Astrophysics collaboration Italian National Institute...
In the framework of USV program, carried on within Italian Aerospace Research Program, a trade-off analysis has been performed aimed at defining configuration and mission profile future experimental Flight Test Bed, called FTB-X, devoted to reentry flight experiments. FTB-X shall exhibit well improved aerodynamic maneuverability characteristics, allowing perform longer endurance re-entry patterns, as compared conventional lifting vehicles, therefore increasing related operability safety...
This paper deals with the experimental investigation on MHD (magneto-hydro-dynamic or magneto-fluid-dynamic) interaction around a test body immersed into hypersonic unseeded air flow. The experiments have been carried out in CIRA plasma wind tunnel SCIROCCO. Two conditions utilized for total pressure of 2.5 and 2.3 bar respectively, specific enthalpy 16 12.1 MJ/kg respectively. flow was accelerated nozzle up to Mach 10. magnetic induction field is generated by an electromagnet enclosed...
In supersonic and hypersonic flows, thermal chemical non-equilibrium is one of the fundamental aspects that must be taken into account for accurate characterization plasma. this paper, we present an optimized methodology to approach plasma numerical simulation by state-to-state kinetics calculations in a fully 3D Navier-Stokes CFD solver. Numerical simulations expanding flow are presented aimed at comparing behavior models with respect macroscopic thermochemical usually used computation high...
An important aspect to be taken into account in the design of a re-entry vehicle is evaluation effects rarefaction on aerodynamic coefficients and heat flux. The lift drag if high efficiency required. At altitudes (or rarefied regimes) decrease an increase occur. Also moments can different from those continuum regime, implying stability behavior. availability reliable during at also for defining trajectory sizing Reaction Control System. It well known that Navier-Stokes equations fail...
This paper deals with the experimental investigation on magneto fluid dynamic interaction around a test body immersed into hypersonic unseeded air flow. The experiments have been carried out in CIRA owned plasma wind tunnel SCIROCCO. Two conditions utilized for experiments, total pressure of 2.5 and 2.3 bar respectively specific enthalpy 16 12.1 MJ/kg, flow accelerated nozzle up to Mach 10. magnetic induction field is generated by an electromagnet enclosed article, can reach 0.8 T maximum...
These paper deals with the numerical rebuilding of experimental data from campaing on blunt body equipped an electromagnet made in CIRA at SCIROCCO facility. A set resticted condition have been considered for rebuilding. Two different codes used, CAST and EMC3NS. Codes, whose structure is generally similar, are some modeling aspects. Their results compared analized criticallycompared, gives a guidelines further developments analysis this field.
The influence of the local effects rarefaction on prediction main parameters typical Shock Wave - Boundary Layer Interaction are presented and analyzed. Slip flow boundary conditions have been implemented in CIRA CFD code H3NS, results compared with available wind tunnel experiments DSMC results. Finally, an experimental test case, planned Plasma Wind Tunnel facility, has analyzed order to check possible rarefaction.
An aerodynamic, computational study has been performed on the 3.9.2_FW50 configuration of winged experimental flying test bed (FTB-X) an unmanned space vehicle in altitude interval 90—110 km, where is transitional regime. The range angle attack was 0—40° and side slip 15°. flow field solved by three-dimensional (3D) direct simulation Monte Carlo (DSMC) code: DS3V. results showed better aerodynamic behaviour both symmetric side-slip flights, but worst longitudinal stability flight with...
The most suitable method to compute aerodynamic forces of a spacecraft, at first stage design, relies on bridging formulae. There are two kinds formulae: global and local. formulae rely knowledge spacecraft force coefficients in continuum free molecular flow. local calculate the skin friction pressure body surface; then computed by integration. aim this work is analyze widely accepted Potter Kotov. To purpose, simple body, like sphere, has been preliminary considered results have compared...
One of the most challenging problems modern aerospace engineering is prediction hypersonic flows, both for complexity required physical modelling and impossibility to duplicate in wind tunnel real flight conditions due high energy levels required. Experimental numerical investigation techniques must be combined mutually validated improved. In frame ESA-EXPERT programme, main goal Payload #07 design execute a experiment on shock-wave boundarylayer interaction with flow reattachment control...
Post-combustion in the reacting plume of a typical solid rocket motor (SRM) is characterized by emission high-temperature gases including pollutants such as hydrochloric acid and chlorine together with particles alumina associated combustion aluminum impregnated original propellant. In this paper, methods modeling an experimental engine, proposed AVIO S.p.A., are studied, where post-combustion location temperature estimates particular interest. The chemical kinetics have been simulated using...
This paper describes the Design of Experiment to study laminar-turbulence transition phenomenon in Hypersonic regime on a 3-deg half-angle sphere-cone model. The huge number factors (as bluntness, distributed roughness, Mach and Reynolds numbers, etc.), that affect laminar-turbulent transition, makes this very complex expensive with typical experimental approach. As consequence, Modern Of approach was adopted develop highly efficient experiment designs yielding results within specified...