Conceptual Advanced Transport Aircraft Design Configuration for Sustained Hypersonic Flight

Alkaya, Can; Sam, Ashish Alex; Pesyridis, Apostolos

doi:10.3390/aerospace5030091

Cited by 13 publications

(9 citation statements)

References 13 publications

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“…An efficient SERN geometry was obtained through 2D and 3D parametric analysis and through 3D combustion modelling of the scramjet. It provides further detailed analysis to the overall aircraft configuration published previously as part of this project by References [2,4,[32][33][34].…”

Section: Discussionmentioning

confidence: 99%

Modelling a Hypersonic Single Expansion Ramp Nozzle of a Hypersonic Aircraft through Parametric Studies

2018

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This paper aims to contribute to developing a potential combined cycle air-breathing engine integrated into an aircraft design, capable of performing flight profiles on a commercial scale. This study specifically focuses on the single expansion ramp nozzle (SERN) and aircraft-engine integration with an emphasis on the combined cycle engine integration into the conceptual aircraft design. A parametric study using computational fluid dynamics (CFD) have been employed to analyze the sensitivity of the SERN’s performance parameters with changing geometry and operating conditions. The SERN adapted to the different operating conditions and was able to retain its performance throughout the altitude simulated. The expansion ramp shape, angle, exit area, and cowl shape influenced the thrust substantially. The internal nozzle expansion and expansion ramp had a significant effect on the lift and moment performance. An optimized SERN was assembled into a scramjet and was subject to various nozzle inflow conditions, to which combustion flow from twin strut injectors produced the best thrust performance. Side fence studies observed longer and diverging side fences to produce extra thrust compared to small and straight fences.

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Section: Discussionmentioning

confidence: 99%

Modelling a Hypersonic Single Expansion Ramp Nozzle of a Hypersonic Aircraft through Parametric Studies

2018

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“…Aerospace 2020, 7, x FOR PEER REVIEW 4 of 18 same project by Neill and Pesyridis [13]. The FAME aircraft requirements have been previously described by Alkaya et al [14]. The individual component analyses on which this work is based, for ramjet and scramjet compression systems have been reported in [15][16][17] and for nozzle performance in [18,19].…”

Section: Dual-mode Combustion Enginesmentioning

confidence: 99%

Modelling of a Dual-Fuel-Mode Free-Jet Combustion System

2019

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The focus of this study is to design a combustion system able to sustain hypersonic flight at Mach 8. A Dual-Mode Free-Jet combustion chamber design, first tested in 2010 by NASA, is being adapted to run on hydrogen fuel instead of ethylene while addressing the excessive thermal heat load. This study is part of the FAME (Flight at Mach Eight) project, with the primary objective to design and analyse the engine configuration for a hypersonic commercial aircraft. This CFD analysis and validation study, the first to replicate this combustion chamber design, provides detailed instructions on the combustion system design. The analysis from this study can be used for future research to successfully reach a sustainable design and operation of a Dual-Mode Free-Jet combustion chamber. The 53% size reduction in the combustion system represents significant progress which encourages future research regarding in the design of combustion systems for hypersonic propulsion systems.

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“…8 On the other hand, supersonic/hypersonic commercial flight is coming back into the attention of the companies in the field because of the signs of progress to develop the efficient aerodynamic design and advanced and fuel-efficient propulsions for such flights, 9,10 and this fact boosts some studies to evaluate such an aircraft. 11,12 Yet, the most important obstacle to gain a supersonic/hypersonic flight is to create an advanced fuel-efficient and environmentally friendly propulsion system. 13 As a result, creating aircraft propulsion that can be adaptable to a wide range of flight altitudes and Mach numbers when it is fuel-efficient and low emission is a key factor to create the next generation of aircraft.…”

Section: Introductionmentioning

confidence: 99%

A novel hybrid aircraft propulsion based on the DEA compressor—Part A: Design

Aryana¹

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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This two-part article introduces a novel hybrid propulsion system based on the DEA compressor. The system encompasses a Pulse Detonation TurboDEA as the master engine that supplies several full-electric ancillary thrusters called DEAThruster. The system, called the propulsion set, can be categorized as a distributed propulsion system based on the design mission and number of ancillary thrusters. Part A of this article explains the design process comprising intake, compressor, detonation process, diffuser, axial turbine, and the exit nozzle. The main target is to design a high-performance low emission propulsion system capable of serving in a wide range of altitudes and flight Mach numbers that covers altitudes up to 20,000 m and flight Mach number up to the hypersonic edge. Designing the propulsion set, the design point is considered at the static condition in the sea level. Design results show the propulsion set can satisfy all requirements necessary for its mission.

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Conceptual Advanced Transport Aircraft Design Configuration for Sustained Hypersonic Flight

Cited by 13 publications

References 13 publications

Modelling a Hypersonic Single Expansion Ramp Nozzle of a Hypersonic Aircraft through Parametric Studies

Modelling a Hypersonic Single Expansion Ramp Nozzle of a Hypersonic Aircraft through Parametric Studies

Modelling of a Dual-Fuel-Mode Free-Jet Combustion System

A novel hybrid aircraft propulsion based on the DEA compressor—Part A: Design

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