Experimental Study of Shock Oscillation over a Transonic Supercritical Profile

Jacquin, Laurent; Molton, Pascal; Deck, Sébastien; Maury, Bernard; Soulevant, Didier

doi:10.2514/1.30190

Cited by 236 publications

(147 citation statements)

References 13 publications

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“…These trends and ndings are generally supported by existing experimental studies [3,13,17], however the available experimental data is insucient for a proper comparison and validation of the computational results. It is noted that the previously suggested [21] necessary criteria for shock-buet onset conditions to take place existed for all simulations in this study.…”

Section: Resultssupporting

confidence: 70%

3D and Finite-wing Effects on the Shock-buffet Instability Mechanism

Iovnovich¹,

Raveh²

2012

53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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A study of the transonic shock-buet ow instability phenomena is presented.Reynolds-averaged Navier-Stokes simulations of four wing congurations are conducted at sock-buet ow conditions. The simulated congurations include nite, innite, straight and swept 3D wing models. Based on the results, the eects of 3D ow and wing niteness on the shock-buet phenomena characteristics are identied. The shock motion typical frequencies, amplitudes, periodicity, continuity and harmonization characteristics are found to be aected by the studied eects. Nevertheless, the instability fundamental mechanism was shown to remain similar to its 2D nature. It was indicated that the previously suggested necessary criteria for shock-buet onset in terms of shock position and ow separations remained relevant for the studied congurations. Swept wings with a tip chord that is parallel to the root chord were found less likely to experience shock-buet compared to similar wings with rotated tip planes.Two unsteady phenomena which are characterized by typical frequencies which are considerably higher than the shock-buet typical frequencies were observed in this study. Nomenclature a ∞ = speed of sound, m/s AR = wing aspect ratio b = wing span, m C L = airfoil lift coecient C p = pressure coecient c = chord length, m f = shock-buet frequency, Hz f = 2πf c/U ∞ = shock-buet reduced frequency I = computational domain index in the chord direction J = computational domain index in the span direction K = computational domain index in the surface normal direction M ∞ = free-stream Mach number R ∞ = free-stream Reynolds number, based on chord t = physical time, s t = a∞t c = nondimensional time U ∞ = free-stream velocity, m/s α = angle of attack, deg α i = induced angle of attack, deg α ∞ = free-stream angle of attack, deg ∆C L = lift coecient amplitude ∆X s = shock travel distance normalized to the chord length ∆t = nondimensional computational time step τ = mean-ow equations ctitious computational time step τ t = turbulence equations ctitious computational time step y + = dimensionless wall distance X = chordwise coordinate normalized to the chord length Y = spanwise coordinate normalized to the chord length 2 Downloaded by MONASH UNIVERSITY on November 26, 2014 | http://arc.aiaa.org |

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Section: Resultssupporting
confidence: 70%

3D and Finite-wing Effects on the Shock-buffet Instability Mechanism
Iovnovich¹,
Raveh²
2012
53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
1
0
2
0
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“…Examples from wind tunnel tests include a shock buffet reduced frequency of 0.49 for the 18% circular arc (McDevitt et al, 1976), and 0.38-0.55 for the NACA0012 airfoil (McDevitt and Okuno, 1985). Recent wind tunnel investigations on supercritical airfoils report reduced frequencies of 0.21 for the OAT15A airfoil (Jacquin et al, 2009), and 0.37 for a swept wing with a BAC 3-11 airfoil (Steimle et al, 2008). These shock buffet reduced frequencies are on the order of typical reduced frequencies of aeroelastic phenomena associated with the first bending/torsion structural modes of airplanes flying at transonic speeds.…”

Section: Introductionmentioning
confidence: 93%

“…Therefore one may expect some mutual shock buffet-structural elastic motion interaction. Furthermore, there is evidence from recent wind tunnel testing that the shock buffet phenomenon is essentially two dimensional (Jacquin et al, 2009). Therefore it is likely that a two-dimensional study can contribute to understanding nonlinear aeroelastic phenomena that are encountered in-flight.…”

Section: Introductionmentioning
confidence: 99%

Frequency lock-in phenomenon for oscillating airfoils in buffeting flows
Raveh
¹
,
Dowell
²

2011
Journal of Fluids and Structures
71
1
25
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“…They examined the onset of unsteadiness on a NACA0012 airfoil undergoing a slow increase in angle of attack at constant Mach number. Meanwhile, this type of investigation was conducted on supercritical SC(2)-0714 [2] and OAT15A [3] airfoils. These studies demonstrate the existence of steady flow at lower angles of attack, giving way to large-scale buffeting above some critical value.…”

Section: Introductionmentioning
confidence: 99%

Predicting the onset of flow unsteadiness based on global instability
Crouch
¹
,
Garbaruk
²
,
Magidov
³

2007
Journal of Computational Physics
232
20
166
1
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Experimental Study of Shock Oscillation over a Transonic Supercritical Profile

Cited by 236 publications

References 13 publications

3D and Finite-wing Effects on the Shock-buffet Instability Mechanism

3D and Finite-wing Effects on the Shock-buffet Instability Mechanism

Frequency lock-in phenomenon for oscillating airfoils in buffeting flows

Predicting the onset of flow unsteadiness based on global instability

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