Borrelli R.,Italian Aerospace Research Center Scpa |
Riccio A.,Italian Aerospace Research Center Scpa |
Tescione D.,Italian Aerospace Research Center Scpa |
Gardi R.,Italian Aerospace Research Center Scpa |
Marino G.,Italian Aerospace Research Center Scpa
Journal of Aerospace Engineering | Year: 2010
The nose cap demonstrator named Nose-2 has been tested for the second time in the plasma wind tunnel (PWT) facility which is part of the sharp hot structure (SHS) technology project, focused on the assessment of the applicability of ultrahigh temperature ceramics (UHTC) to the fabrication of high performance vehicles and SHS for reusable launch vehicles. In this paper the FEM based thermal analyses, carried out for the rebuilding of this PWT test, are presented. Experimental data measured in the PWT have been compared with numerical ones in order to validate the FEM model and to help in interpreting the experimental test itself. The knowledge on the physical phenomenon under investigation has been greatly improved, thanks to the synergy between numerical and experimental activities. In particular, a qualitative study of the modeling of the tip-dome interface has been performed in order to estimate the thermal contact resistance that heat flux encounters in passing through the demonstrator. The correlation between numerical and experimental temperature curves has been found to be satisfactory for both internal and surface temperature distribution, and the FEM model was found reliable in reproducing the thermal behavior of the nose cap. © 2010 ASCE.
Cinquegrana D.,Italian Aerospace Research Center Scpa |
Petrosino F.,Italian Aerospace Research Center Scpa |
Pezzella G.,Italian Aerospace Research Center Scpa |
Capizzano F.,Italian Aerospace Research Center Scpa |
And 3 more authors.
45th AIAA Plasmadynamics and Lasers Conference | Year: 2014
This paper deals with the aerodynamic and aerothermodynamic analysis of a conceptual aeroshape, designed to fit the constraints of VEGA launcher fairing and with the capability to perform an end-to-end mission from launch, orbit keeping, re-entry and landing on conventional runway. Aerodynamic and aerothermodynamic performances of the aeroshape under investigation were evaluated for the whole flight scenario by means of several numerical simulations with in-house developed and commercial codes. Compilation of the numerical Data-Base, consisting of about 170 runs, and vehicle's aerodynamics performances are shown from low subsonic to hypersonic regime. Analysis and discussion of the results with comparisons between different numerical tools and CFD codes are given.