|
French National Center for Scientific Research / Centre National de la Recherche Scientifique (CNRS)
|
|
|
Address:
|
3 Michel-Ange street, CNRS, Paris, PO: 75794, Ile-de-France (France)
|
Institut de Combustion Aérothermique Réactivité et Environnement - Institut for Combustion, Aerothermics, Reactivity and Environment.
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.
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.
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.
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.
