Project Title

Next Generation Supersonic Candidate Engine and Aircraft Design

Presenters

Academic department under which the project should be listed

SPCEET - Industrial and Systems Engineering

Faculty Sponsor Name

Adeel Khalid

No students were used in this project.

Abstract (300 words maximum)

The objective of this design study/competition - Next Generation Supersonic Candidate Engine and Aircraft Design, is a response to a proposal and is motivated by NASA’s National Research Announcement in 2006. The requirements of this design study are provided by AIAA (American Institute of Aeronautics and Astronautics). The aircraft designed is a private business class where the aircraft engine and design perform at a maximum speed of Mach 1.8 at 55,000 feet with a range of 4000 nmi. A generated mission profile through considerations in flight regime will drive the design involved in the development of aircraft characteristics. Interior cabin configurations are expected to support seating for up to 100 passengers. Using parametric cycle analysis, computational fluid dynamics, and system modeling/experimentation, a refined aircraft, and engine design will be produced. Detailed analyses to meet the baseline requirements involve interpretation of trends of current generation aircraft engines are considered for the finalized design. The performance of the aircraft engine will involve calculations on wave drag, supersonic turbulent flow, and integrated methods of design of the nacelle enveloped within the aircraft fuselage. Through these various iterative methods, considerations in supersonic aircraft propulsion and aircraft design are presented. Projected technical specifications are to be implemented for the next generation of supersonic aircraft expected to be debuted in 2025. A robust composition of advanced material composites, methods of manufacturing, and forecasted advancements in technology are utilized to develop a proposal for the next generation of supersonic aircraft.

Project Type

Oral Presentation (15-min time slots)

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Next Generation Supersonic Candidate Engine and Aircraft Design

The objective of this design study/competition - Next Generation Supersonic Candidate Engine and Aircraft Design, is a response to a proposal and is motivated by NASA’s National Research Announcement in 2006. The requirements of this design study are provided by AIAA (American Institute of Aeronautics and Astronautics). The aircraft designed is a private business class where the aircraft engine and design perform at a maximum speed of Mach 1.8 at 55,000 feet with a range of 4000 nmi. A generated mission profile through considerations in flight regime will drive the design involved in the development of aircraft characteristics. Interior cabin configurations are expected to support seating for up to 100 passengers. Using parametric cycle analysis, computational fluid dynamics, and system modeling/experimentation, a refined aircraft, and engine design will be produced. Detailed analyses to meet the baseline requirements involve interpretation of trends of current generation aircraft engines are considered for the finalized design. The performance of the aircraft engine will involve calculations on wave drag, supersonic turbulent flow, and integrated methods of design of the nacelle enveloped within the aircraft fuselage. Through these various iterative methods, considerations in supersonic aircraft propulsion and aircraft design are presented. Projected technical specifications are to be implemented for the next generation of supersonic aircraft expected to be debuted in 2025. A robust composition of advanced material composites, methods of manufacturing, and forecasted advancements in technology are utilized to develop a proposal for the next generation of supersonic aircraft.