The high-speed experimental flight test vehicle of HEXAFLY-INT: a multidisciplinary design

Benedetto, Sara Di; Donato, M. P. Di; Schettino, Antonio; Scigliano, Roberto; Nebula, Francesco; Morani, Gianfranco; Cristillo, D.; Marini, Marco; Cardone, Salvatore; Steelant, Johan; Villace, Victor Fernandez

doi:10.1007/s12567-020-00341-5

Cited by 6 publications

(2 citation statements)

References 12 publications

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“…In past years, some innovative high-speed aircraft configurations have been proposed and evaluated in depth, with the main goal of demonstrating the economic viability of a high-speed aircraft fleet [44][45][46][47][48]. These concepts make use of unexploited flight routes in the stratosphere, offering a solution to the presently congested flight paths while ensuring minimal environmental impact in terms of emitted noise and greenhouse gasses, particularly during the stratospheric cruise phase.…”

Section: Case Study No 1: Stratofly Mr3 Hypersonic Vehiclementioning

confidence: 99%

Numerical Simulation of Heat Pipe Thermal Performance for Aerospace Cooling System Applications

Scigliano,

De Simone,

Fusaro

et al. 2024

Aerospace

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The design of integrated and highly efficient solutions for thermal management is a key capability for different aerospace products, ranging from civil aircraft using hydrogen on board to miniaturized satellites. In particular, this paper discloses a novel numerical tool for the design and thermal performance assessment of heat pipes. To achieve this goal, a numerical Ansys Parametric Design Language code is set up to verify the effective subtractive heat flux guaranteed by the selected heat pipe arrangement. The methodology and related tool show their ability to provide good thermal performance estimates for different heat pipe designs and operating conditions. Specifically, the paper reports two very different test cases: (1) solid metal heat pipes to cool down the crotch leading-edge area of the air intake of a Mach 8 civil passenger aircraft, and (2) a copper-water heat pipe to cool down a Printed Circuit Board of a generic small LEO satellite. The successful application of the methodology and numerical code confirms the achievement of the ambitious goal of developing in-house tools to support heat pipe thermal performance prediction for the entire aerospace domain.

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Section: Case Study No 1: Stratofly Mr3 Hypersonic Vehiclementioning

confidence: 99%

Numerical Simulation of Heat Pipe Thermal Performance for Aerospace Cooling System Applications

Scigliano,

De Simone,

Fusaro

et al. 2024

Aerospace

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“…An alternative application of the suborbital flights is a point to point transportation. Studies on both spaceport and vehicles can be found in [3][4][5] and [6] The researchers from the Warsaw University of Technology were inspired by the Ansary X-Prize competition and begun to work on their own concept of vehicle for manned suborbital tourism flights [7,8]. The MAS (Modular Airplane System) project consists of two airplanes-a mother plane and a rocket plane (see Fig.…”

Section: Introductionmentioning

confidence: 99%

An investigation into directional characteristics of the rocket plane in a tailless configuration

Kwiek

Figat

2022

CEAS Space J

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This paper embraces result of wind tunnel tests of a rocket plane designed to space tourism application. The rocket plane is designed in a tailless configuration with a leading edge extension (LEX) and side plates on the wing’s tip which work as all moving tail. Usually for such a concept of control, movable surfaces are position in a horizontal direction while in the considered concept there is no classical rudder, and the movable surfaces are mounted with a significant dihedral angle. The research was carried out in the subsonic closed circuit wind tunnel with an open test section. Moreover, MGAERO and PANUKL package were used for numerical computations. The first research question is to investigate how the configuration of the side plate affects the directional stability of the rocket plane. The second aim is to study the efficiency of the side plates deflected like an all moving tail for both low and high angles of attack. As a result of this investigation, the directional stability derivatives and the control derivatives were obtained. Finally, the experimental results were compared with numerical outcomes to establish does software with no full flow model can be applicable for design an aircraft with all moving tail in case of low of angles of attack.

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Linearly combined transition model based on empirical spot growth correlations

2023

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The transition from laminar to turbulent flow in a hypersonic boundary layer is modeled using an intermittency-based linear combination approach. A simplified transition model like this enables a quick assessment of aero-thermal loads and the overall flight efficiency of high-speed vehicles during the initial design phase by weighting purely laminar and turbulent flow results on the basis of an empirically calculated intermittency. The transition model presented within this work includes an empirical model to account for Mach number, Reynolds number, wall temperature and pressure gradient effects on turbulent spot growth based on available turbulent spot studies in the literature. A validation of the transition model is carried out for a number of different test cases and a methodology to extend the model to generic geometries is presented to enable a more general application.

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The high-speed experimental flight test vehicle of HEXAFLY-INT: a multidisciplinary design

Cited by 6 publications

References 12 publications

Numerical Simulation of Heat Pipe Thermal Performance for Aerospace Cooling System Applications

Numerical Simulation of Heat Pipe Thermal Performance for Aerospace Cooling System Applications

An investigation into directional characteristics of the rocket plane in a tailless configuration

Linearly combined transition model based on empirical spot growth correlations

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