Transonic Buffet Simulation over Supercritical Airfoil by Unsteady-FaSTAR Code

2016 ◽  
Author(s):  
Takashi Ishida ◽  
Keiichi Ishiko ◽  
Atsushi Hashimoto ◽  
Takashi Aoyama ◽  
Kuniyuki Takekawa
Keyword(s):  
Supercritical Airfoil ◽  
Transonic Buffet

Numerical Study of Transonic Buffet on a Supercritical Airfoil

AIAA Journal ◽  
2006 ◽  
Vol 44 (3) ◽  
pp. 620-628 ◽  
Author(s):  
Q. Xiao ◽  
H. M. Tsai ◽  
F. Liu
Keyword(s):  
Numerical Study ◽  
Supercritical Airfoil ◽  
Transonic Buffet

scholarly journals Experimental investigation of the transonic buffet cycle on a supercritical airfoil

2021 ◽  
Vol 62 (10) ◽  
Author(s):  
A. D’Aguanno ◽  
F. F. J. Schrijer ◽  
B. W. van Oudheusden
Keyword(s):  
Travelling Waves ◽  
Short Exposure ◽  
Main Peak ◽  
Small Scale ◽  
Trailing Edge ◽  
Cycle Frequency ◽  
Supercritical Airfoil ◽  
Shock Oscillation ◽  
Transonic Buffet ◽  
Good Agreement

Abstract Transonic buffet behaviour of the supercritical airfoil OAT15A was investigated experimentally at flow conditions $$Ma=0.7$$ M a = 0.7 and $$\alpha =3.5^\circ $$ α = 3 . 5 ∘ , using schlieren and particle image velocimetry (PIV). The general behaviour of the buffet cycle was characterised with short-exposure schlieren visualisation and phase-averaged PIV measurements. A spectral analysis showed that the shock oscillation occurs with a dominant contribution at 160 Hz (St = 0.07, in good agreement with the literature) and between 25 and 55 % of the chord of the airfoil. Proper Orthogonal Decomposition (POD) was applied to the PIV data to extract the main modes connected with buffet. It is found that the first three most energetic modes capture around 65 % of the total fluctuating kinetic energy. The first and the third modes have a main frequency peak at 160 Hz and are well representing the separated area and the shock oscillation. The second mode was, instead, associated with an asymmetrical behaviour of the separated area and of the shear layer and displays a main peak at 320 Hz, being double the main buffet cycle frequency. Finally, it was shown that by using the 11 most energetic POD modes, an accurate reduced-order model (ROM) is obtained, which when subtracted from the instantaneous velocity fields allows the visualisation of the small-scale structures present in the flow, such as the upstream travelling waves (UTWs) and the vortex shedding in the separated area near the trailing edge. The analysis allowed to estimate the velocity of the UTWs, obtaining values in good agreement with the literature. In contrast, the analysis of the vortex dynamics in the trailing edge area revealed that vortices shed at the shock foot, which convect downstream in an area detached from the airfoil surface, cannot be considered responsible for the creation of UTWs in view of the mismatch in frequency of the two phenomena. Graphic abstract

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