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Collaborative Aircraft Design Methodology using ADAS linked to CEASIOM
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Aerodynamics. (flygteknik)ORCID iD: 0000-0003-4991-5503
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Aerodynamics.
2014 (English)In: 32nd AIAA Applied Aerodynamic Conference, 2014Conference paper (Refereed)
Abstract [en]

The aircraft design stages, conceptual and preliminary, are necessarily collaborative bytheir very nature. An example design carried out in this paper brings the collaborativeaspects of design to life by two academic groups, one in Naples and one in Stockholm, usingtheir own tools ADAS and CEASIOM, working respectively on conceptual and preliminarydesign. The ADAS tool is primarily empirically-based design methodology, and the CEA-SIOM tool is primarily physics-based design methodology. The example chosen is a FAR-23compliant 16-seat twin turboprop aircraft. The high-wing configuration resulting from theADAS conceptual design is the down-selected to CEASIOM where a water-tight model of thegeometry is constructed, a volume grid is generated and 16 flight conditions are simulatedby solutions of the Euler equations, some with propeller off, and others with propellerin order to judge the effect of the propeller wash over the main wing and horizontal tailsurface. Detailed comparisons between ADAS results and CEASIOM results for stability &control characteristics are carried out. In general there is reasonable agreement betweenthe two sets, considering that the empiricisms in ADAS account for viscous effects where asthe CEASIOM are purely inviscid (but nonlinear). The largest discrepancy appears in thepitching moment contribution from the horizontal tail, and various explanations for thisare suggested, including possible effects of the main wing downwash and wake on the tail.

Place, publisher, year, edition, pages
Keyword [en]
Collaborative aircraft design, ADAS, CEASIOM, Euler computation, actuator disk model
National Category
Aerospace Engineering
Research subject
Aerospace Engineering
URN: urn:nbn:se:kth:diva-168164DOI: 10.2514/6.2014-2012ScopusID: 2-s2.0-84903904013OAI: diva2:814535
32nd AIAA Applied Aerodynamics Conference 2014; Atlanta, GA; United States; 16 June 2014 through 20 June 2014

QC 20150527

Available from: 2015-05-27 Created: 2015-05-27 Last updated: 2015-06-10Bibliographically approved
In thesis
1. Contributions to Variable Fidelity MDO Framework for Collaborative and Integrated Aircraft Design
Open this publication in new window or tab >>Contributions to Variable Fidelity MDO Framework for Collaborative and Integrated Aircraft Design
2015 (English)Doctoral thesis, comprehensive summary (Other academic)
Abstract [en]

The thesis develops computational tools for early stages of the aircraft design process. The work focuses on a framework which allows several design teams concurrently to develop a baseline concept into a configuration which meets requirements and whose aerodynamics has been assessed by flight simulation. To this end, a data base format suggested by the German Aerospace Center DLR was adopted in the CEASIOM system, developed in the EU 6th Framework Program, enabling more accurate transonic analysis and tabulation of forces and moments as well as control surface authority assessment. Results from simple, fast models are combined with computationally expensive full CFD results by co-Kriging to speed up productionof the aero-data for flight simulation.

Non-linear optimization methods in wing design play an increasingly important role together with computational aerodynamics. High performance computing enables the use of high-fidelity non-linear flow predictions in optimization loops. It is argued that the optimization tools should allow the engineer to influence the process by setting up suitable target pressure distributions for the shape to approach, combined with steps to minimize drag under suitable constraints on geometry, forces, and moments. The simulation framework incorporated into CEASIOM was applied to a number of configurations, conventional as well as un-conventional, such as an a-symmetric twin prop, a canard-configured transonic cruiser, and a novel chinrudder concept for transonic airliners. Aerodynamic shape design by the developed methods was applied to the standard M6 benchmark wing, a joined-wing concept, a wing-tip, and a blended wing-body.

Abstract [sv]

Avhandlingen utvecklat beräkningsmoduler för tidiga stadier i flygplanskonstruktionsprocessen. Arbetet kocentreras på ett program-ramverk som låter flera designteam samtidigt utveckla en grund-modell till en konfiguration som uppfyller ställda krav och vars aerodynamik har undersökts med flygsimulering. För att nå detta mål antogs ett data-bas format utarbetat av DLR (German Aerospace Center) i CEASIOM-programpaketet som utvecklats i EUs sjätte ramprogram. Det möjliggjorde noggrannare analys och framtagning av tabeller över krafter och moment liksom bedömning av styrytors funktion i transoniskt fartområde. Resultat från enkla, snabba beräknngsmodeller kombineras via co-Kriging med beräkningsmässigt dyra CFD-körningar för att snabbt ta fram aero-data som behövs för flygsimuleringen.

Icke-linjär optimering spelar allt större roll i ving-formgivning, tillsammans med numerisk aerodynamik. Högpresterande datorer medger användning av noggranna icke-linjära strömningsmodeller också i optimerings-slingor. Det argumenteras för att optimerings-verktygen skall ge ingenjörerna direkt inflytande över processen genom definition av fördelaktiga tryckfördelningar som vingformen ska åstadkomma, kombinerat med steg som minimerar luftmotstånd under bivillkor på geometri, krafter och moment.

Simulerings-ramverket implementerat i CEASIOM tillämpas så på ett antal konfigurationer, konventionella såväl som o-konventionella: ett osymmetriskt tvåmotorigt propellerplan, och större transoniska flygplan, ett för Mach 0.97 med canardvinge, och ett nytt koncept med hak-roder.

Aerodynamisk formgivning med de utvecklade metoderna tillämpas på standardfallet M6-vingen, en transonisk dubbel-vinge, en vingtipp, och en flygande vinge.

Place, publisher, year, edition, pages
Stockholm: KTH Royal Institute of Technology, 2015. xx, 101 p.
TRITA-AVE, ISSN 1651-7660 ; 2015:27
National Category
Aerospace Engineering
Research subject
Aerospace Engineering
urn:nbn:se:kth:diva-168169 (URN)978-91-7595-606-0 (ISBN)
Public defence
2015-06-12, F3, Lindstedtsvägen 26, KTH, Stockholm, 10:15 (English)

QC 20150528

Available from: 2015-05-28 Created: 2015-05-27 Last updated: 2015-05-28Bibliographically approved

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