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Roncioni P.,Aerospace Propulsion and Reacting Flows Unit | Ranuzzi G.,Aerospace Propulsion and Reacting Flows Unit | Marini M.,Aerospace Propulsion and Reacting Flows Unit | Paris S.,Von Karman Institute for Fluid Dynamics | And 2 more authors.
Journal of Spacecraft and Rockets | Year: 2011

The main results of the aerothermodynamic hypersonic characterization of the intermediate experimental vehicle, by means of both computational fluid dynamics simulations and wind-tunnel measurements, have been reported and analyzed in this work, developed in the frame of ESA Future Launcher Preparatory Program. A test campaign has been carried out at the von Kármán Institute Free Piston Longshot wind tunnel in a cold hypersonic regime. The numerical simulations, rebuilding the von Kármán Institute wind-tunnel conditions, have been performed by the Italian Aerospace Research Center, the goal being to support the procedure of extrapolation-to-flight of the measurements and the general aerothermal characterization. A detailed comparison of all measured and predicted hypersonic relevant phenomena and aerothermodynamic parameters, such as surface pressure and heat flux, is reported in the paper, together with a detailed description of the configuration, freestream conditions, and model attitude effects. The reproducibility of flight conditions in the von Kármán Institute Longshot test campaign is qualitatively very good, both in terms of flow features and surface properties as indicated by wind-tunnel numerical simulations. The comparisons of numerical and experimental results indicate a good agreement in terms of external flow structure, i.e., bow shock, shock layer, expansion at the junction on windward side, shock-wave boundary-layer interaction in the flap area, and multiple-shock interaction above the flap. Sideslip, angle-of-attack, and flapdeflection effects are correctly reproduced by computational fluid dynamics in terms of pressure coefficient and heat flux. Copyright © 2010 by the American Institute of Aeronautics and Astronautics, Inc.

Votta R.,Aerospace Propulsion and Reacting Flows Unit | Marini M.,Aerospace Propulsion and Reacting Flows Unit | De Filippis F.,Space Systems Unit | Di Vice M.,Aeronautical Systems Unit | Sabatano R.,Space Systems Unit
Journal of Spacecraft and Rockets | Year: 2010

A feasibility study of ExoMars parachute supersonic experiment to be possibly performed in the Centro Italiano Ricerche Aerospaziali Plasma Wind-Tunnel Scirocco facility has been analyzed. To verify the test feasibility, some test conditions in terms of facility reservoir conditions have been simulated by means of computational fluid dynamics computations of a modified nozzle, and verified with respect to testing requirements mainly in terms of test article size, Mach number, and dynamic pressure. The proper functioning of the wind tunnel has also been checked. In particular, the facility makes available a80-MWpower vacuum system that guarantees inside the test chamber the low-pressure conditions of the Mars atmosphere into which the parachute is foreseen to be opened. The possibility to introduce an air heater and/or burner would assure also the matching of temperature requirement, and reduce the request of mass flow rate. Computational fluid dynamics simulations of the complete facility configuration (nozzle, test chamber, diffuser) with the test article inside have verified the right functioning of the diffuser (occurrence of tunnel blockage) and the effects of the interaction between the bow shock wave in front of the capsule and the flow exiting from the nozzle, and the pressure that establishes inside the test chamber. © 2010 by CIRA S.c.p. A. (Italian Aerospace Research Centre). Published by the American Institute of Aeronautics and Astronautics, Inc.

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