This paper deals with the fundamental results of the first loop of design and aerodynamic analysis of a new regional turboprop concept. The aircraft has a low wing and two innovative architecture of turboprop engine installed at the horizontal tail tips. It can seat up to 130 passengers with a design range of about 3000km. It is designed to fly at Mach number of about 0.62 at a cruise altitude of 9000m with an efficiency about 18. The required maximum lift coefficients in clean, take-off and landing conditions are 1.6, 2.4 and 3.0 respectively. Wing sections have been specifically designed to comply with the very challenging requirements in terms of minimum drag (natural laminar flow), maximum clean lift coefficients and compressibility effects. The high lift devices have been designed too. A single fowler flap layout has been considered. To augment the aircraft maximum lift capabilities in landing condition, preserving the wing laminar flow, the effects of a simple droop nose have been investigated. To improve climb performance a specific winglet design has been assessed, results show that a reduction of about 10% of the induced drag during both climb and cruise phase could be achieved. All the criticalities emerged during the first loop will feed a second design loop to well asses this innovative concept.

Design and aerodynamic analysis of a regional turboprop innovative configuration / Nicolosi, F; Corcione, S; Della Vecchia, P; Trifari, Vittorio; Ruocco, M; De Marco, A.. - Unico:(2017), pp. 1-16. (Intervento presentato al convegno 6th CEAS Air and Space Conference tenutosi a Bucharest (ROMANIA) nel 16-20 October 2017).

Design and aerodynamic analysis of a regional turboprop innovative configuration

Nicolosi F;Corcione S;Della Vecchia P;Trifari, Vittorio;Ruocco M;De Marco A.
2017

Abstract

This paper deals with the fundamental results of the first loop of design and aerodynamic analysis of a new regional turboprop concept. The aircraft has a low wing and two innovative architecture of turboprop engine installed at the horizontal tail tips. It can seat up to 130 passengers with a design range of about 3000km. It is designed to fly at Mach number of about 0.62 at a cruise altitude of 9000m with an efficiency about 18. The required maximum lift coefficients in clean, take-off and landing conditions are 1.6, 2.4 and 3.0 respectively. Wing sections have been specifically designed to comply with the very challenging requirements in terms of minimum drag (natural laminar flow), maximum clean lift coefficients and compressibility effects. The high lift devices have been designed too. A single fowler flap layout has been considered. To augment the aircraft maximum lift capabilities in landing condition, preserving the wing laminar flow, the effects of a simple droop nose have been investigated. To improve climb performance a specific winglet design has been assessed, results show that a reduction of about 10% of the induced drag during both climb and cruise phase could be achieved. All the criticalities emerged during the first loop will feed a second design loop to well asses this innovative concept.
2017
Design and aerodynamic analysis of a regional turboprop innovative configuration / Nicolosi, F; Corcione, S; Della Vecchia, P; Trifari, Vittorio; Ruocco, M; De Marco, A.. - Unico:(2017), pp. 1-16. (Intervento presentato al convegno 6th CEAS Air and Space Conference tenutosi a Bucharest (ROMANIA) nel 16-20 October 2017).
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Descrizione: Articolo CEAS 2017 ID 893
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11588/696609
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