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Facilities for Aerothermodynamics and Supersonic Technologies Platform (FAST)
Identification
Hosting Legal Entity
French National Center for Scientific Research
Address:
3 Michel-Ange street, CNRS, Paris, PO: 75794, Ile-de-France (France)
Location
1 C Avenue de la Recherche Scientifique, Laboratoire ICARE INSIS, CNRS, Orléans, PO: 45071, Region Centre (France)
Structure
Type Of RI
Single-sited
Coordinating Country
France
Status
Status
Current Status:
Operational since 1965
Timeline
Being upgraded since 2000
Scientific Description
The experimental platform FAST, ‘Facilities for Aerothermodynamics and Supersonic Technologies’ includes a set of three facilities, MARHy, PHEDRA and EDITH, which research fields focus on investigation of the properties of the hypersonic and supersonic gas flow surrounding a spacecraft during the crossing of the upper layers of a planetary atmosphere. These low pressure facilities are complementary and they allow accomplishing in the same laboratory the study of different aspects of the atmospheric entry like aerodynamic, strength, heat flux, high enthalpy radiation, ionization and fundamental physics on non-equilibrium transfer.

RI Keywords
Edith, Supersonic, Mach, Aerodynamics, Marhy, Plasma, Reynolds, High-enthalpy, Wind tunnels, Hypersonich, Rarefied, Phedra
Classifications
RI Category
Aerospace and aerodynamics research facilities
Scientific Domain
Engineering and Energy
Services
Access to ICARE Laboratory

Institut de Combustion Aérothermique Réactivité et Environnement - Institut for Combustion, Aerothermics, Reactivity and Environment.

Equipment
Main diagnostic tools

Optical spectroscopy (VUV-Visible-IR), Langmuir probes, infrared thermography (heat fluxes, surface temperature), aerodynamic balances, imaging CCD camera, Pitot probes, Schlieren visualization, time of flight, thermocouples, fast pressure transducers.

Supersonic wind tunnel EDITH

Main featuresWorking gas: Reservoir Air at 300 Bar Other nozzles and operation conditions can easily be adapted Model Span, cm 10 Extensive adaptor for individual model and probe mounting Typical tests and investigations Fundamental research on shock waves Aerodynamic and aerothermal behavior of probes and models. Fluidic thrust vectoring of supersonic nozzle.

Supersonic / hypersonic rarefied wind tunnel MARHy

Main features Continuous hypersonic/supersonic rarefied wind tunnel. 5m x 2.5m test chamberNozzle: contoured and conical Adjustable pumping group, max capacity: 153 000 m3/h Static pressure, Pa:10-2 Pstg 71 Stagnation pressure, Pa: 20 Po 120 Stagnation temperature, K: 300 To 1300Mach number : 0.8 Mach 20Reynolds number /cm: 26.3 Re 7522 Kundsen number /cm: 1.2 10-2 Kd 0.11 Altitude similitude (earth), km: 20 h 136 Model Span 10 cm Extensive adaptor for individual model and probe mounting Typical tests and investigations Fundamental research of fluid dynamic phenomena in rarefied compressible flows. Aerodynamic and aerothermal behavior of probes and models. Interaction of thrust exhaust plume with spacecraft surfaces. Supersonic/hypersonic plasma flow control at rarefied conditions simulating high altitude atmospheric entries. Experimental data base for validation of DSMC and BGK codes.

Supersonic high enthalpy rarefied wind tunnel (arc-jet) PHEDRA

Main features Continuous supersonic high enthalpy rarefied wind tunnel. 4.5m x 2.1 m test chamber Nozzle: conical Adjustable pumping group, max capacity: 26 000 m3/h Static pressure, Pa: 1 Pstg 3000 Stagnation pressure, Pa: 20 Po 120 Mach number: 2 Mach 8 Averaged enthalpy, Mj/kg: few Ho 55 Working gas: N2, Air, CO2, CH4, Ar and extensive mixturesModel 5Span, cm 10 Typical tests and investigations Fundamental research of high enthalpy fluid dynamic phenomena in non-equilibrium flows. Experimental data base on planetary atmospheric entries: Mars, Earth, Titan, Venus. Aerodynamic and aerothermal behavior of probes and models. MHD Plasma flow control.

Date of last update: 16/05/2017