Aerodynamic database development of the ESA intermediate experimental vehicle

Pezzella, Giuseppe; Marino, Giuseppe; Rufolo, Giuseppe C.

doi:10.1016/j.actaastro.2013.07.019

Cited by 20 publications

(6 citation statements)

References 5 publications

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“…To test and further develop the technologies and concepts produced by these studies, there was a clear need to accumulate practical flight experience. To this end, ESA has undertaken the design of the intermediate experimental vehicle (IXV) also promoted within the FLPP framework [22]. It was derived by the Pre-X concept investigated early by CNES [23].…”

Section: Past Developmentsmentioning

confidence: 99%

Introductory Chapter: Hypersonic Vehicles - Past, Present, and Future Insights

Viviani¹,

Pezzella²

2019

Hypersonic Vehicles - Past, Present and Future Developments

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Section: Past Developmentsmentioning

confidence: 99%

Introductory Chapter: Hypersonic Vehicles - Past, Present, and Future Insights

Viviani¹,

Pezzella²

2019

Hypersonic Vehicles - Past, Present and Future Developments

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“…Each contribute is based on a small number of parameters, as recognized herein. Further, as done in the past for the US Orbiter and X-34 vehicles, the EFTV AM development relies on the following applicable assumptions 21 : 1. Only rigid body aerodynamic coefficients are evaluated, i.e., no aero-elastic deformations are accounted for; 2.…”

Section: The Aerodynamic Model Of the Eftv Glidermentioning

confidence: 99%

Numerical and Experimental Aerodynamic Characterization of the HEXAFLY-INT Hypersonic Glider

Marini¹,

Pezzella²,

Schettino³

et al. 2017

21st AIAA International Space Planes and Hypersonics Technologies Conference

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As a fundamental step towards the development of a civil high-speed transport concept, the European Community (EC) co-funded HEXAFLY-INT international project (with partners from Europe, Russian Federation, Brazil and Australia), has the aim to design, manufacture and test in flight an innovative gliding hypersonic vehicle, based on the configuration developed in previous EC co-funded projects LAPCAT I, II and HEXAFLY. The flight experiment is focused on a self-controlled glider configuration characterized by high aerodynamic efficiency and equipped with several breakthrough technologies on-board, in order to provide valuable aerodynamic and aero-structural flight data to validate methods and technologies used to design the hypersonic vehicle. In this framework, this paper provides a detailed overview on research efforts carried out in assessing the aerodynamic performance of the expendable Experimental Flight Test Vehicle under development in the programme. Aerodynamic results are obtained by means of a massive number of CFD simulations of increasing level of accuracy and through an experimental test campaign carried out at TsAGI in their T-116 wind tunnel facility.

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“…To this end, a non-canonical geometry, as shown in figure 1, is the focus of the present work. This geometry is inspired by earlier designs used in previous suborbital (Martellucci & Weinberg 1982;Oberkampf & Aeschliman 1992;Walker & Rodgers 2005) and orbital (Massobrio et al 2007;Pezzella, Marino & Rufolo 2014) hypersonic reentry-body studies.…”

Section: Introductionmentioning

confidence: 99%

Relaminarization effects in hypersonic flow on a three-dimensional expansion–compression geometry

Pandey,

Casper,

Beresh

2024

J. Fluid Mech.

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This experimental work explores the flow field around a three-dimensional expansion–compression geometry on a slender cone at Mach 8 using high-frequency pressure sensors, high-frame-rate schlieren, temperature-sensitive paint, shear-stress measurements and oil-flow visualizations. The $7^\circ$ cone geometry has a hyperbolic slice which acts as an expansion corner and suppresses the disturbances present in the upstream boundary layer. Downstream of the cone-slice corner, high-frequency boundary-layer disturbances attenuate in all cases. Under laminar conditions, second-mode instabilities from the cone diminish and lower-frequency second-mode waves develop on the slice at a frequency commensurate with the increased boundary layer thickness. For fully turbulent cases, the boundary layer over the slice shows evidence of a two-layered nature with a turbulent outer region and a near-wall region with strong attenuation of high-frequency disturbances and reappearance of lower-frequency instability waves. When a downstream compression ramp is added to the slice, the expanded boundary layer shows enhanced susceptibility to separation such that separation is observed at a $10^{\circ }$ deflection, which is smaller than expected for turbulent conditions. For a $30^{\circ }$ ramp, boundary-layer separation occurs further upstream where the heat flux contours show a decrease in heating that is characteristic of a transitional separation. These results demonstrate the effect of relaminarization caused by an upstream expansion on a subsequent shock-wave/boundary-layer interaction.

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Aerodynamic database development of the ESA intermediate experimental vehicle

Cited by 20 publications

References 5 publications

Introductory Chapter: Hypersonic Vehicles - Past, Present, and Future Insights

Introductory Chapter: Hypersonic Vehicles - Past, Present, and Future Insights

Numerical and Experimental Aerodynamic Characterization of the HEXAFLY-INT Hypersonic Glider

Relaminarization effects in hypersonic flow on a three-dimensional expansion–compression geometry

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