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Characterization of Wall Temperature Effect during Transition of Hypersonic flow over a Cone By Experiments And Numerical Simulations

Characterization of Wall Temperature Effect during Transition of Hypersonic flow over a Cone By Experiments And Numerical Simulations

Objective

The development of secure and re-usable re-entry vehicle requires the complete control of the heat distribution on its Thermal Protection System (TPS).
During the most critical re-entry phase, the hypersonic flow along the vehicle initiates a laminar boundary layer inside of which most of the transfer phenomena take place (heat, momentum and mass transfer). If at one position of the vehicle, this boundary layer experiences a transition from the laminar to the turbulent regime then at the corresponding position the TPS will receive a sharp increase of the incoming heat flux (minimum 3 times higher). If the vehicle aims to be re-usable, it is mandatory to protect it adequately against this overheat. Therefore Aerospace designer needs to receive the proper information and tools allowing a better prediction and ultimately a better control of the transition in hypersonic regime.
This activity proposes a detailed and careful experimental and numerical data base from six hypersonic facilities and several numerical codes from EU and Russia. The selected configuration will be the one of a sharp cone. The noise level in each facility will be characterised. The probable differences between facility predictions running at seemingly comparable conditions (Mach number, Reynolds number and model dimensions) will be explained.
Various types of numerical simulations including DNS will be carried out to prepare the experimental campaigns. These simulations will be further validated and assess during the activity.
Hypersonic transition will be observed with and without localized control. A deeper understanding of the physics involved in hypersonic transition will be investigated. The challenging solution of the local thermal control of the boundary layer at hypersonic regime will be proposed for future aerospace mission and disseminated in the industrial community.
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Coordinator

INSTITUT VON KARMAN DE DYNAMIQUE DES FLUIDES

Address

Chaussee De Waterloo 72
1640 Rhode Saint Genese

Belgium

Activity type

Research Organisations

EU Contribution

€ 119 999

Administrative Contact

Patrick Rambaud (Prof.)

Participants (4)

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FEDERALNOE GOSUDARSTVENNOE UNITARNOPREDPRIYATIE TSENTRALNY NAUCHNO- ISSLEDOVATELSKY INSTITUT MACHINOSTROENIYA

Russia

EU Contribution

€ 84 000

DEUTSCHES ZENTRUM FUER LUFT - UND RAUMFAHRT EV

Germany

EU Contribution

€ 145 000

SA KHRISTIANOVICH INSTITUTE OF THEORETICAL AND APPLIED MECHANICS OF SIBERIAN BRANCH OF RUSSIAN ACADEMY OFSCIENCE*ITAM OF SB RAS

Russia

EU Contribution

€ 80 000

FEDERAL STATE UNITARY ENTERPRISE THE CENTRAL AEROHYDRODYNAMIC INSTITUTE NAMED AFTER PROF. N.E. ZHUKOVSKY

Russia

EU Contribution

€ 71 000

Project information

Grant agreement ID: 263182

Status

Closed project

  • Start date

    1 June 2011

  • End date

    31 May 2013

Funded under:

FP7-SPACE

  • Overall budget:

    € 651 373

  • EU contribution

    € 499 999

Coordinated by:

INSTITUT VON KARMAN DE DYNAMIQUE DES FLUIDES

Belgium

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