Within the frame of the LAPCAT II project (Long-term Advanced Propulsion Concepts and Technologies, funded by the European Commission as part of the 7th Frame Program and involving 16 European research labs and industries), four concurrent system studies have been carried out to design a Mach 8 vehicle able to carry passengers on the Brussels-Sydney route. The required range is above 18000 km, and the defined number of passengers is 300, which correspond to a 60 tons / 1400 m3 payload. Inspired by the previous analysis led by Onera on PREPHA-based concepts 1, by the University of Rome on TBCC hypersonic performances 2, 3 and by Université Libre de Bruxelles on precooled turbofan performances 4, a deeper analysis on a LH2 turbofan/ramjet/scramjet concept was performed, including a parametric sizing of the vehicle, a more detailed internal layout and especially a step-by-step numerical analysis of the aeropropulsive performances on the Mach 8 cruise point, using a nose-to-tail approach. These steps will be described in the paper. © 2011 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

LAPCAT-II: Conceptual design of a mach 8 TBCC civil aircraft, enforced by full navier-stokes 3D nose-to-tail computation / Sebastien, Defoort; Marc, Ferrier; Serre, Laurent; Dominique, Scherrer; Paridaens, Christophe; Patrick, Hendrick; Ingenito, Antonella; Bruno, Claudio. - (2011). (Intervento presentato al convegno 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011 tenutosi a San Francisco; United States nel 11 April 2011 through 14 April 2011) [10.2514/6.2011-2317].

LAPCAT-II: Conceptual design of a mach 8 TBCC civil aircraft, enforced by full navier-stokes 3D nose-to-tail computation

INGENITO, ANTONELLA;BRUNO, Claudio
2011

Abstract

Within the frame of the LAPCAT II project (Long-term Advanced Propulsion Concepts and Technologies, funded by the European Commission as part of the 7th Frame Program and involving 16 European research labs and industries), four concurrent system studies have been carried out to design a Mach 8 vehicle able to carry passengers on the Brussels-Sydney route. The required range is above 18000 km, and the defined number of passengers is 300, which correspond to a 60 tons / 1400 m3 payload. Inspired by the previous analysis led by Onera on PREPHA-based concepts 1, by the University of Rome on TBCC hypersonic performances 2, 3 and by Université Libre de Bruxelles on precooled turbofan performances 4, a deeper analysis on a LH2 turbofan/ramjet/scramjet concept was performed, including a parametric sizing of the vehicle, a more detailed internal layout and especially a step-by-step numerical analysis of the aeropropulsive performances on the Mach 8 cruise point, using a nose-to-tail approach. These steps will be described in the paper. © 2011 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
2011
17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011
Civil aircrafts; Concurrent systems; European Commission
04 Pubblicazione in atti di convegno::04b Atto di convegno in volume
LAPCAT-II: Conceptual design of a mach 8 TBCC civil aircraft, enforced by full navier-stokes 3D nose-to-tail computation / Sebastien, Defoort; Marc, Ferrier; Serre, Laurent; Dominique, Scherrer; Paridaens, Christophe; Patrick, Hendrick; Ingenito, Antonella; Bruno, Claudio. - (2011). (Intervento presentato al convegno 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011 tenutosi a San Francisco; United States nel 11 April 2011 through 14 April 2011) [10.2514/6.2011-2317].
File allegati a questo prodotto
Non ci sono file associati a questo prodotto.

I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.

Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11573/412514
 Attenzione

Attenzione! I dati visualizzati non sono stati sottoposti a validazione da parte dell'ateneo

Citazioni
  • ???jsp.display-item.citation.pmc??? ND
  • Scopus 12
  • ???jsp.display-item.citation.isi??? ND
social impact