Control of transonic periodic flow on NACA0012 aerofoil by contour bumps

Tulita, Catalin; Raghunathan, Srinivasan; Bénard, Emmanuel

doi:10.1007/978-94-010-0017-8_44

Cited by 4 publications

(11 citation statements)

References 6 publications

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“…Figure 2 (a) and 2(b) show the model of a circular arc blade with bump on the blade for without angle of attack (θ = 0°) and with angle of attack (θ = 3.2°, 8.5°) to the free stream flow, respectively. The bump has length and height of 10% and 2% of blade chord length, respectively [4]. The crest of the bump is located at the position Table 1.…”

Section: Governing Equationsmentioning

confidence: 99%

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Transonic moist air flow around a circular arc blade with bump

et al. 2009

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The unsteady phenomena in the transonic flow around airfoils are observed in the flow field of fan, compressor blades and butterfly valves, and this causes often serious problems such as aeroacoustic noise and the vibration.In recent years, the effect of bump wall on the flow field around an airfoil has been investigated experimentally and as a result, it was observed that the bump wall is effective for the control of shock wave on the airfoil. In the transonic or supersonic flow field, a rapid expansion of moist air or steam gives rise to non-equilibrium condensation. In the present study, the effect of non-equilibrium condensation of moist air on the self-excited shock wave oscillation around a circular arc blade with or without a bump on the blade was investigated numerically. The results showed that the non-equilibrium condensation significantly reduced the flow field unsteadiness such as root mean of pressure oscillation and frequency compared to the case without the non-equilibrium condensation.

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Section: Governing Equationsmentioning

confidence: 99%

“…Among them, bump wall on the blade is considered as an effective control technique [4][5]. In high speed aerodynamics, expansion of vapor/carrier gas mixture (moist air) or steam is often so rapid (cooling rate ≈ 1k/μs) that the non-equilibrium condensation will occur after a supersaturated state is attained [6][7][8].…”

Section: Introductionmentioning

confidence: 99%

Transonic moist air flow around a circular arc blade with bump

et al. 2009

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“…The current CFD techniques for prediction of periodic transonic flows (2)(3)(4)(5)(6)(7)(8)(9)22,24,(31)(32)(33)(34)(35) are primarily based on two methods. The first method consists of solving the time accurate Reynolds Averaged Navier-Stokes (RANS) equations (24,26,29,38,40) directly using an implicit or explicit numeric scheme in conjunction with algebraic or non-linear turbulence models (or, more recently, using Large Eddy Simulation, LES). The second method is the interactive boundary-layer coupling method (15,22) and involves the solution of an outer inviscid region and an inner viscous boundary-layer which is coupled through the boundary condition on the wing and wake.…”

Section: Prediction Of Periodic Transonic Flowmentioning

confidence: 99%

“…In the case of the NACA0012 aerofoil with a RANS approach, all three kinds of periodic motion were identified on the upper surface of the aerofoil ranging between Mach 0⋅7 and 0⋅8, at different angles of incidence and Reynolds numbers based on chord ranging from 1 to 14 × 10 6 (38) . For example, at M = 0⋅775, Re = 10 × 10 6 and four degrees incidence with a Baldwin-Lomax turbulence model, a type B periodic motion was observed.…”

Section: Naca 0012 Aerofoilmentioning

confidence: 99%

Periodic transonic flow and control

et al. 2008

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The current understanding of periodic transonic flow is reviewed briefly. The effects of boundary-layer transition, non-adiabatic wall conditions and modifications to the aerofoil surface geometry at the shock interactions on periodic transonic flow are discussed. Through the methods presented, it is proposed that the frequency of periodic motion can be predicted with reasonable accuracy, but there are limitations on the prediction of buffet boundaries associated with periodic transonic flows. Several methods have been proposed by which the periodic motion may be virtually eliminated, most relevantly by altering the position of transition fix, contouring the aerofoils surface or adding a porous surface and a cavity in the region of shock interaction. In addition, it has been shown that heat transfer can have a significant effect on buffet.

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“…The following NS-type, laminar, unsteady hyperbolic matrix equation system is written for both the gas fraction and the condensed part of the fluid mixture, and stands for example as the background of the Eagle solver (Tulita et al, 2002), used in many previous aerodynamic investigations at QUB and UPB. A single type of condensed particles is considered, in other words the chemical interactions are seen as minimal and not interfering with the flow process.…”

Section: Equations Governing the Exo-atmospheric Erosionmentioning

confidence: 99%