Numerical simulations and performance assessment of a scramjet powered cruise vehicle at Mach 8

Roncioni, Pietro; Natale, Pasquale; Marini, Marco; Langener, Tobias; Steelant, Johan

doi:10.1016/j.ast.2015.01.006

Cited by 48 publications

(10 citation statements)

References 8 publications

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“…An interesting approach towards the identification of the physical characteristics of the machines is also provided in (7) , where a theoretical approach is suggested for the estimation of some dimensionless parameters of turbomachines based on the Cordier diagram. The main governing equations presented in (11) the paper have been a starting point of the proposed work together with relationships relating the dimensionless parameters to each other. Semiempirical methods for the estimation of the turbopump mass and volume (8) have been selected as they provide a useful base for semi-empirical predictive models, besides considering some very specific operational ranges.…”

Section: Existing Estimation Modelsmentioning

confidence: 99%

“…hypersonic cruiser concept resulting from multiple design optimizations performed within the European Projects LAPCAT I and LAPCAT II (2) . The vehicle is characterized by a waverider configuration, and it is equipped with six Air Turbo Rockets (ATRs) (9,10) and one Dual Mode Ramjet (DMR) (11) , which allows cruising at Mach 8 at an altitude above 33,000 m following the mission profile specified in Fig. 1.…”

Section: Lapcat Mr2mentioning

confidence: 99%

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A methodology for preliminary sizing of a Thermal and Energy Management System for a hypersonic vehicle

et al. 2019

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This paper addresses a methodology to parametrically size thermal control subsystems for high-speed transportation systems during the conceptual design phase. This methodology should be sufficiently general to be exploited for the derivation of Estimation Relationships (ERs) for geometrically sizing characteristics as well as mass, volume and power budgets both for active (turbopumps, turbines and compressors) and passive components (heat exchangers, tanks and pipes). Following this approach, ad-hoc semi-empirical models relating the geometrical sizing, mass, volume and power features of each component to the operating conditions have been derived. As a specific case, a semi-empirical parametric model for turbopumps sizing is derived. In addition, the Thermal and Energy Management Subsystem (TEMS) for the LAPCAT MR2 vehicle is used as an example of a highly integrated multifunctional subsystem. The TEMS is based on the exploitation of liquid hydrogen boil-off in the cryogenic tanks generated by the heat load penetrating the aeroshell throughout the point-to-point hypersonic mission. Eventually, specific comments about the results will be provided together with suggestions for future improvements.

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Section: Existing Estimation Modelsmentioning

confidence: 99%

Section: Lapcat Mr2mentioning

confidence: 99%

A methodology for preliminary sizing of a Thermal and Energy Management System for a hypersonic vehicle

et al. 2019

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“…A full 3D CFD analysis was carried out for the stand-alone combustor, taking into account various injector holes located on each of the 23 struts (total of 1248 holes) Figure 29 shows some details on mesh-grid adopted for the discrete hole geometry taken from [55], [52] and [53].…”

Section: Figure 26: Left: Fan Geometry With Density Filed On the Suctmentioning

confidence: 99%

“…The aero-propulsive balance for the MR2 was verified by means of Nose-To-Tail computations of the entire MR2.4 configuration based upon various CFD codes at the design (M8) and off-design flight Mach number[50][51][52][53]…”

mentioning

confidence: 99%

Achievements Obtained for Sustained Hypersonic Flight within the LAPCAT-II project

Steelant¹,

Varvill²,

Defoort³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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The design of hypersonic airbreathing vehicles is a challenging objective due to the intrinsic complexity of propulsion-airframe integration in combination with an engine cycle design able to operate over a wide Mach number range. This is one of the objectives of EC co-funded project LAPCAT-II aiming to reduce antipodal flights to less than 2 to 4 hours. Among the several studied vehicles in the preceding project LAPCAT-I, only aircraft designs for Mach 5 and 8 flights were retained in the present project. Starting from the available Mach 5 vehicle and its related pre-cooled turbo-ramjet, assumed performance figures of different components were now assessed in more detail numerically and experimentally. Though the cruise flight of the Mach 8 vehicle based on a scramjet seemed feasible, further refinement was needed. In support to the integrated vehicle design, dedicated aerodynamic and propulsive experiments were done for the different components as well as for the complete vehicle. This included also the mutual verification of the windtunnels within Europe. In parallel, modelling implementation and validation on high-speed aerodynamics and propulsion were performed. The validated tools gave confidence to assess the performances of the fully integrated vehicles to comply with the mission goals. Finally, the impact of the emissions onto the climate was evaluated. Nomenclature

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“…In the development of hypersonic flight systems, several types of air-breathing engines for different application layers, such as scramjets [1,2], dual-mode scramjets [3,4], and combined-cycle engines [5,6], have long been studied.…”

Section: Introductionmentioning

confidence: 99%

Study of thermal throat of RBCC combustor based on one-dimensional analysis

Wang

Qin

et al. 2015

Acta Astronautica

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Numerical simulations and performance assessment of a scramjet powered cruise vehicle at Mach 8

Cited by 48 publications

References 8 publications

A methodology for preliminary sizing of a Thermal and Energy Management System for a hypersonic vehicle

A methodology for preliminary sizing of a Thermal and Energy Management System for a hypersonic vehicle

Achievements Obtained for Sustained Hypersonic Flight within the LAPCAT-II project

Study of thermal throat of RBCC combustor based on one-dimensional analysis

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