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Creation and Validation of Early Stage Conceptual Design Methodology for Blended WingBody Aircraft
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
2019 (English)Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
Abstract [en]

The current design paradigm for developing tube-and-wing style aircraft has been well documented in literature. This research attempts to develop and val-idate a similar design methodology to what is presently utilized for tube-and-wing based aircraft, but has so far not been successfully implemented for the blended wing-body. This construction has no clear distinction between the lift generating surfaces and the cargo carrying structure. The methodology that was developed included the concatenation and validation of low-fidelity, low speed and low complexity aerodynamic models in order to allow for quick and simple analysis of a large number of possible geometries. This enables the user eÿciently determine the most promising candidate geometries for further study and/or development. Known issues with the low velocity and low com-plexity aerodynamic models include the absence of shock wave modelling, an important part in determining the aerodynamic performance of a lift generat-ing surface. The result of this work is the creation and documentation of a procedure for early-stage design of a blended wing-body airframe. However, due to convergence issues with the high-fidelity CFD solver, the methodology could not been validated for transonic flow. It can thus be only considered valid for flow velocities for which the Prandtl-Glauert correction is valid.

Abstract [sv]

Den befintliga konstruktionsmetodiken för utveckling och design av flygfarkoster är väl dokumenterad i tidigare publicerad litteratur. Detta arbete ämmar utveckla och validera en liknande metodologi som redan existerar för de väl etablerade flygplansgeometrier som baseras på cylinder/vingar-principen. Metoden som utvecklades inkluderade sammansättaning och validering av tidigare existerande lågupplösta samt lågkomplexa aerodynamiska modeller avsedda för beräkning av flödesekvationer för inkompressibel, friktionsfri och stationär strömning. Detta var avsett att möjliggöra ögonblicksvalidering av en föreslagen sammansmält kropp/vinge-geometri med speciell fokus på vissa prestationsbaserade nyckeltal. För cylinder/vinge-geometrier är dessa lågupplösta metoder i litteraturen väletablerat inexakta på grund av en avsaknad av stötvågsmodellering, men då stora delar av de lyftkraftsgenererande ytorna för-ändrats på en sammansmält kropp/vinge är inte nödvändigtvis detta sant för den typen av flygplan också. Då de högupplösta, mer komplexa höghastighetssimuleringarna inte konvergerade inom den utsatta tiden kan den föreslagna metodiken endast anses giltig för det intervall av flödeshastighet vari PrandtlGlauerts korrektionsfaktor stämmer väl överens med verkligheten.

Place, publisher, year, edition, pages
2019. , p. 56
Series
TRITA-SCI-GRU ; 2019:287
National Category
Aerospace Engineering
Identifiers
URN: urn:nbn:se:kth:diva-261700OAI: oai:DiVA.org:kth-261700DiVA, id: diva2:1359787
External cooperation
Institut Supérieur de l’Aéronautique et de l’Espace, Toulouse,
Examiners
Available from: 2019-10-10 Created: 2019-10-10 Last updated: 2019-10-10Bibliographically approved

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