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Aerothermal analysis of an advanced hot structure for hypersonic flight tests

Published online by Cambridge University Press:  01 February 2011

Raffaele Savino ,
Mario De Stefano Fumo ,
Giuliano Marino  and
Mario Tului
Raffaele Savino
Affiliation:
Dept. of Space Science and Engineering (DISIS), University of Naples (Italy)
Mario De Stefano Fumo
Affiliation:
Dept. of Space Science and Engineering (DISIS), University of Naples (Italy)
Giuliano Marino
Affiliation:
Centro Italiano Ricerche Aerospaziali (CIRA), Capua (Italy)
Mario Tului
Affiliation:
Centro Sviluppo Materiali (CSM), Roma (Italy)
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Abstract

This paper deals with the aerothemodynamic analysis of an advanced concept of hot structure to be investigated in the Expert flight test programme.

Three-dimensional fluid dynamic computations have been carried out at the flight conditions of the reference Expert trajectory to evaluate the aerothermodynamic field and the thermal loads on the winglet. The physical model includes viscous effects, real gas properties, non equilibrium chemical reactions and surface catalytic effects. The unsteady aerothermal analysis has been carried out considering different thermal boundary conditions (adiabatic wall or thermal coupling with the capsule metallic skin).

The results are discussed with particular attention to the temperature distributions in the Ultra High Temperature Ceramics (UHTC) and in the structural support.

Type
Research Article
Information
MRS Online Proceedings Library (OPL) , Volume 851: Symposium NN – Materials for Space Applications , 2004 , NN11.5
Copyright
Copyright © Materials Research Society 2005

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References

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