Implementation of Propulsion System Integration Losses to a Supersonic Military Aircraft Conceptual Design

Emre Karaselvi, Melike Nikbay*

*Corresponding author for this work

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

Abstract

This paper presents an early stage integration of propulsion system into multidisciplinary aircraft design process by accounting various types of drag forces generated by intake, engine and nozzle key parameters. An in-house code has been developed empirical formulas and will be supported by CFD analysis for inlet, engine and nozzle components. For engine uninstalled performance, F119-PW-100 like engine performance cycle deck modeled with Numerical Propulsion System Simulation (NPSS) software. For the intake, 2D caret type, fixed intake is considered and for the nozzle, 2D nozzle performance assumptions are used to calculate losses due to the installation of the propulsion system.

Original languageEnglish
Title of host publicationAIAA Propulsion and Energy Forum, 2021
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624106118
DOIs
Publication statusPublished - 2021
EventAIAA Propulsion and Energy Forum, 2021 - Virtual, Online
Duration: 9 Aug 202111 Aug 2021

Publication series

NameAIAA Propulsion and Energy Forum, 2021

Conference

ConferenceAIAA Propulsion and Energy Forum, 2021
CityVirtual, Online
Period9/08/2111/08/21

Bibliographical note

Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

Funding

The three authors would like to thank the NATO STO AVT-333 (Integration of Propulsion, Power, and Thermal Subsystem Models into Air Vehicle Conceptual Design) research task group for their collaboration. The first author would also like to thank Turkish Aerospace Industry for the support for this paper.

FundersFunder number
Turkish Aerospace Industry
North Atlantic Treaty OrganizationSTO AVT-333

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