Theoretical and Experimental Studies on High-Temperature Ionized Gas Flows around Thermal Protection Systems for Space Vehicles

Información del proyecto

Identificador del acuerdo de subvención: INTAS-RFBR95-1329

Fecha de inicio

Fecha de finalización

Financiado con arreglo a

• International Association for the promotion of cooperation with scientists from the independent states of the former Soviet Union (INTAS), 1993-

Coste total

Sin datos

Aportación de la UE

Sin datos

Coordinado por

Von Karman Institute for Fluid Dynamics
Belgium

Objetivo

In the framework of the project it is proposed
1. to create a complex model describing chemical, vibrational, electron, and electronic nonequilibrium in partially dissociated and ionized air;
2. to develop a model for the interaction between a multi-species multi-temperature rarefied gas and the non-disintegrating surface of a re-entry vehicle with heterogeneous reactions and slip in the Knudsen layer taken into account;
3. to develop a new multi-temperature model of radiation;
4. to create an effective computer code for the simulation of real-gas effects past hypersonic vehicles on the basis of the Viscous Shock Layer equations model;
5. to create an effective computer code for the simulation of real-gas effects in RF-induction heated plasmatrons, on the basis of the full Navier-Stokes equations, with and without coupling to Maxwell equations for a time-averaged RF electromagnetic field;
6. to test the models discussed by comparing the numerical calculations with experimental data obtained in plasmatrons;
7. to carry-out large-scale numerical investigations of hypersonic flows past blunt axisymmetric bodies at zero and small angles of attack at uniform and non-uniform free-stream conditions. This will be done in order to assess quantitatively how the effects of multi-species diffusion, chemical and relaxational kinetics under thermal nonequilibrium, slip in the Knudsen layer, and heterogeneous reactions, influence macroscopic flow characteristics (pressure, temperature, chemical composition, heating rates, shock stand-off distance, radiation spectral intensities, etc.).
The project is aimed at the development of a complete mathematical model of the physico-chemical processes occurring in the shock layer over a hypersonic vehicle and on its surface. The model should adequately reflect physical reality, should give unambiguous data on flow characteristics, and it should be simple enough to be implemented in engineering calculations.
The created codes will combine advantages of the best modern physical approaches for the simulation of real-gas phenomena with the high effectiveness of the numerical and experimental simulation methods developed by the six teams of participants in the project.
The objectives of the project will be achieved by coupling theoretical work of the research groups with experimental activity and systematic numerical investigations, using state-of-the art physico-chemical models supplied by the other groups. This will be fostered through a continuous exchange of information and results and mutual visits, within the limitations imposed by the project grant.
The results will be presented as scientific papers and reports.

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Programa(s)

• IC-INTAS - International Association for the promotion of cooperation with scientists from the independent states of the former Soviet Union (INTAS), 1993-

Tema(s)

• 6 - Engineering Sciences, Aeronautics, Space

Convocatoria de propuestas

Datos no disponibles

Régimen de financiación

Datos no disponibles

Coordinador

Von Karman Institute for Fluid Dynamics

• Aportación de la UE: Sin datos
• Dirección: 1640 Rhode-St-Genese ; Bélgica
• Coste total: Sin datos

Participantes (1)

Moscow State University ' M.V. Lomonosov '

Rusia

• Aportación de la UE: Sin datos
• Dirección: 119899 Moscow
• Coste total: Sin datos