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Abstract
This work investigates limit cycle oscillations in the transonic regime. A novel approach to predict Limit Cycle Oscillations using high fidelity analysis is exploited to accelerate calculations. The method used is an Aeroeasltic Harmonic Balance approach, which has been proven to be efficient and able to predict periodic phenomena. The behaviour of limit cycle oscillations is analysed using uncertainty quantification tools based on polynomial chaos expansions. To improve the efficiency of the sampling process for the polynomialchaos expansions an adaptive sampling procedure is used. These methods are exercised using two problems: a pitch/plunge aerofoil and a deltawing. Results indicate that Mach n. variability is determinant to the amplitude of the LCO for the 2D test case, whereas for the wing case analysed here, variability in the Mach n. has an almost negligible influence in amplitude variation and the LCO frequency variability has an almost linear relation with Mach number. Further test cases are required to understand the generality of these results.
Original language  English 

Publication status  Published  Oct 2014 
Event  4th EASN Workshop on Flight Physics and Aircraft Design  Germany, Aachen, Germany Duration: 27 Oct 2014 → 29 Oct 2014 
Conference
Conference  4th EASN Workshop on Flight Physics and Aircraft Design 

Country/Territory  Germany 
City  Aachen 
Period  27/10/2014 → 29/10/2014 
Keywords
 CFD
 Harmonic Balance
 aeroelasticity
 Nonlinear
ASJC Scopus subject areas
 Aerospace Engineering
 Computational Mechanics
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Dive into the research topics of 'Investigation of Limit Cycle Oscillations Using AeroelasticHarmonic Balance Method'. Together they form a unique fingerprint.Projects
 1 Finished

R1191AER: ENACT  Efficient nonlinear Aeroelasticity Computations under Uncertainty
Marques, S.
01/08/2012 → 31/12/2014
Project: Research