Aerodynamic Characterization of Hypersonic Transportation Systems and Its Impact on Mission Analysis

Viola, Nicole; Roncioni, Pietro; Gori, Oscar; Fusaro, Roberta

doi:10.3390/en14123580

Cited by 11 publications

(12 citation statements)

References 9 publications

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“…The parameters α, β, and γ can be customized depending on the vehicle configuration. For example, the values α = 0.43, β = 0.31, and γ = 0.37 were found for the STRATOFLY MR3 configuration [30]. Moreover, a preliminary direct comparison of the results of the previous formulations with both viscous CFD and experimental measurements can be found in Figure 2, where the drag coefficient of another vehicle of the MORE&LESS project (CS2 of Figure 3) is reported (less than 7% difference).…”

Section: Low-fidelity Aerodatabasementioning

confidence: 79%

“…At the first stage, the aerodynamic modeling consists of the investigation of the clean configuration (with undeflected control surfaces). Based on the experience gained in the H2020 STRATOFLY project (Horizon 2020 STRATOspheric FLYing Opportunities for High-Speed Propulsion Concepts Project), inviscid CFD simulations are used on the clean configuration, and then properly tailored viscous effects corrections are applied [30]. These corrections can be estimated through engineering formulations, which are widely available in the literature and whose coefficients can be tuned to properly capture the peculiarities of the vehicle and its flight trajectory.…”

Section: Low-fidelity Aerodatabasementioning

confidence: 99%

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Aerodatabase Development and Integration and Mission Analysis of a Mach 2 Supersonic Civil Aircraft

Roncioni,

Marini,

Gori

et al. 2024

Aerospace

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The request for faster and greener civil aviation is urging the worldwide scientific community and aerospace industry to develop a new generation of supersonic aircraft, which are expected to be environmentally sustainable and to guarantee a high-level protection of citizens. A key aspect to monitor the potential environmental impact of new configurations is the aerodynamic efficiency and its impact onto the real mission. To pursue this goal, this paper discloses increasing-fidelity aerodynamic modeling approaches to improve the conceptual design of high-speed vehicles. The disclosed methodology foresees the development of aerodynamic aerodatabases by means of incremental steps starting from simplified methods (panels methods and/or low-fidelity CFD simulations) up to very reliable data based on high-fidelity CFD simulations and experimental measurements with associated confidence levels. This multifidelity approach enables the possibility of supporting the aircraft design process at different stages of its design cycle, from the estimation of preliminary aerodynamic coefficients at the beginning of the conceptual design, up to the development of tailored aerodatabases at advanced design phases. For each design stage, a build-up approach is adopted, starting from the investigation of the clean external configuration up to the complete one, including control surfaces’ effects and, if any, the effects of the integration of the propulsive effects. In addition, the applicability of the approach is guaranteed for a wide range of supersonic and hypersonic aircraft, and the developed methodology is here applied to the characterization of Mach 2 aircraft configuration, a relevant case study of the H2020 MORE&LESS project.

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Section: Low-fidelity Aerodatabasementioning

confidence: 79%

Section: Low-fidelity Aerodatabasementioning

confidence: 99%

Aerodatabase Development and Integration and Mission Analysis of a Mach 2 Supersonic Civil Aircraft

Roncioni,

Marini,

Gori

et al. 2024

Aerospace

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“…The Flight Control System (FCS) is considered a key enabler for future high-speed aircraft and, therefore, the anticipation of its impact on aircraft layout and performance is essential to assess the viability of concepts under development. Preliminary investigations carried out in several high-speed projects [1][2][3][4] highlight that a reduction of about 30%, with respect to the maximum theoretical efficiency of a hypersonic civil aircraft, can be expected due to control surface deflection. Therefore, dealing with the effect of the FCS on the vehicle's behavior beforehand, since the early stages of design, guarantees a more accurate and realistic aerodynamic characterization, as well as a consequent more reliable estimation of fuel consumption and range performance.…”

Section: Introductionmentioning

confidence: 99%

Integrated Flight Control System Characterization Approach for Civil High-Speed Vehicles in Conceptual Design

et al. 2023

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Recent studies have revealed that control surface deflection can cause a reduction in the aerodynamic efficiency of a hypersonic aircraft of up to 30%. In fact, the characterization of the Flight Control System is essential for the estimation of the consistent aerodynamic characteristics of the vehicle in different phases, considering the contribution of control surfaces to stability and trim. In terms of the sizing process, traditional methodologies have been demonstrated to be no longer applicable to estimations of the actuation power required for the control surfaces of a high-speed aircraft, due to their peculiar working conditions and to the characteristics of the flow to which they are exposed. In turn, numerical simulation approaches based on computational fluid dynamics or panel methods may require considerable time resources, which do not fit with the needs of the quick and reliable estimates that are typical of the early design phases. Therefore, this paper is aimed at describing a methodology to show how to anticipate the Flight Control System design for high-speed vehicles at the conceptual design stage, properly considering the interactions at vehicle level and predicting the behavior of the system throughout an entire mission. It is also a core part of the work to provide designers with an example of how neglecting the effect of trim drag can be detrimental to a reliable estimation of overall aircraft performance. The analysis, mainly focused on the longitudinal plane of the vehicle, is presented step-by-step on a specific case study, namely the STRATOFLY MR3 vehicle, a Mach 8 waverider concept for civil antipodal flights. The application of the methodology, conceived as an initial step towards an iterative Flight Control System design process, also shows that the most power-demanding phases are take-off, low supersonic acceleration, and approach, where peaks of over 130 kW are reached, while an average of 20 kW is sufficient to support deflections in a hypersonic cruise.

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“…Recently, the high Mach number engine has become one of the most important research directions in aerospace for application in hypersonic aircraft, considered as the long-term future of long-range aviation [1,2], and has attracted lots of research interests [3][4][5][6]. The turbine-based combined cycle engine (TBCC) is a suitable propulsion power for high Mach number aircraft, which is able to provide wide Mach number operation range, reusability, flexibility and horizontal take-off and landing ability [7].…”

Section: Introductionmentioning

confidence: 99%

Parametric Research and Aerodynamic Characteristic of a Two-Stage Transonic Compressor for a Turbine Based Combined Cycle Engine

Shi

2022

Aerospace

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This paper researches the parametric optimization of a two-stage transonic compressor having a large air bypass at partial rotating speed according to flow analysis for a turbine-based combined cycle engine (TBCC). To obtain adequate thrust, the inlet transonic compressor of the turbofan part of the TBCC is required to have a wider frequently used corrected rotating speed range and a larger mass-flow rate at low rotating speed, which is different from a typical transonic compressor. The one-dimensional blade design parameters and flow path of the baseline two-stage transonic compressor are introduced. With the widely used CFD software Numeca, the three-dimensional flow fields of the baseline transonic compressor and effects of the flow path between Stage 1 and Stage 2 on the inlet mass flow rate are analyzed for indicating the further improvement direction. For design speed (NC = 1.0), to improve the efficiency at the design point, parametric research is carried out on Rotor 2 to optimize the shock structure and strength, resulting in enhanced efficiency at the design point due to reduced shock loss of Rotor 2. For partial speed (NC = 0.8 and 0.7), since the flow field analysis indicates that the flow blockage in S1 limits the entire mass flow rate, the parametric redesign of stator S1 aims at obtaining an increased blade throat width to enhance the flow capacity of S1. Simulation confirms the increase in the mass-flow rate and efficiency at partial speed due to the reduction in flow blockage and related viscous losses. Aerodynamic analysis at representative operation points indicates that the modifications of R2 and S1 lead to obvious aerodynamic improvement at all rotating speeds (NC = 1.0 to 0.7), while maintaining sufficient stall margin.

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Aerodynamic Characterization of Hypersonic Transportation Systems and Its Impact on Mission Analysis

Cited by 11 publications

References 9 publications

Aerodatabase Development and Integration and Mission Analysis of a Mach 2 Supersonic Civil Aircraft

Aerodatabase Development and Integration and Mission Analysis of a Mach 2 Supersonic Civil Aircraft

Integrated Flight Control System Characterization Approach for Civil High-Speed Vehicles in Conceptual Design

Parametric Research and Aerodynamic Characteristic of a Two-Stage Transonic Compressor for a Turbine Based Combined Cycle Engine

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