Control of cavity flow oscillation through leading edge flow modification

1998 ◽  
Author(s):  
A. Rona ◽  
X. Chen ◽  
X. Zhang ◽  
J. Edwards
Keyword(s):  
Leading Edge ◽  
Cavity Flow ◽  
Flow Oscillation ◽  
Flow Modification ◽  
Edge Flow

ATTENUATION OF CAVITY FLOW OSCILLATION THROUGH LEADING EDGE FLOW CONTROL

1999 ◽  
Vol 221 (1) ◽  
pp. 23-47 ◽  
Author(s):  
X. Zhang ◽  
X.X. Chen ◽  
A. Rona ◽  
J.A. Edwards
Keyword(s):  
Flow Control ◽  
Leading Edge ◽  
Cavity Flow ◽  
Flow Oscillation ◽  
Edge Flow

Numerical Study on Control of Sunroof Buffeting

2021 ◽  
Vol 13 (2) ◽  
Author(s):  
K. Vijaykumar ◽  
S. Poonkodi ◽  
A.T. Sriram
Keyword(s):  
Numerical Study ◽  
Leading Edge ◽  
Dominant Frequency ◽  
Navier Stokes ◽  
Navier Stokes Equation ◽  
Ansys Fluent ◽  
Flow Modification ◽  
Numerical Result ◽  
Modification Technique ◽  
Commercial Solver

Sunroof has become one of the essential features of a luxury car, and it provides natural air circulation and good illumination into the car. But the primary problem associated with it is the buffeting noise which causes discomfort to the passengers. Though adequate studies were carried out on sunroof buffeting, efficient control techniques are needed to be developed from fundamental mechanism. To reduce the buffeting noise, flow modifications at the entrance of the sunroof is considered in this study. The internal portion of the car with sunroof is simplified into a shear driven open cavity, and two-dimensional numerical simulations are carried out using commercial solver, ANSYS Fluent. Reynolds averaged Navier-Stokes equation is used with the realizable k-? turbulence model. The unsteady numerical result obtained in this study is validated with the available experimental results for the dominant frequency. The prediction is good agreement with experiment. Flow modification technique is proposed to control the sunroof buffeting by implementing geometric modifications. A hump has been placed near the leading edge of the cavity which resulted in significant reduction of pressure oscillations. Parametric studies have been performed by varying the height of hump and the distance of hump from the leading edge. There is no prominent difference when the height of the hump is varied. As the distance of the hump from the leading edge is reduced, the sound pressure level decreases.

Steady Performance of a Flexible Hydrofoil Near a Free Surface

1990 ◽  
Vol 34 (04) ◽  
pp. 302-310
Author(s):  
Salwa M. Rashad ◽  
Theodore Green
Keyword(s):  
Mathematical Model ◽  
Free Surface ◽  
Cavity Length ◽  
Leading Edge ◽  
Cavity Flow ◽  
Cavitation Number ◽  
Deformation Characteristics ◽  
Flow Depth ◽  
Lift And Drag ◽  
The Galerkin Method

A linearized cavity-flow theory is used to develop a mathematical model to study the steady characteristics of a flexible hydrofoil near a free surface. The Galerkin method is employed to account for the mutual interaction between the fluid and structure forces. Cheng and Rott's method [1]2 is used to derive general expressions for the deformation characteristics in steady flow of an arbitrarily shaped hydrofoil, with a clamped trailing edge and free leading edge. From the analysis it is possible to determine the lift and drag coefficients, cavity length, and the foil steady deformation for any given specific foil shape, cavitation number, angle of attack, flow depth/chord ratio and rigidity. Sample numerical results are given, and the effects of flexibility and the proximity of the free surface are discussed. Chordwise flexibility tends to increase drag and decrease lift coefficients. This effect is more serious near the free surface. A slight increase of the thickness near the leading edge diminishes the flexibility effects.

Studies on the Outline of Flow Improvement With Speed Ratio in a Counter Rotating Turbine

2019 ◽  
Author(s):  
Rayapati Subbarao ◽  
M. Govardhan
Keyword(s):  
Skin Friction ◽  
Nodal Point ◽  
Leading Edge ◽  
Suction Side ◽  
Tip Clearance ◽  
Speed Ratio ◽  
Flow Topology ◽  
Current Effort ◽  
Pressure Surface ◽  
Flow Modification

Abstract Flow through the Counter Rotating Turbine (CRT) stage is more complex due to the presence of two rotors that rotate in the opposite direction, the spacing between them and the tip clearance provided on rotors. This flow aspect may change, if we change the parameters like speed, spacing and blade angles. Current effort contains simulation studies on the flow topology of CRT through dissimilar speed ratios in the range of 0.85–1.17. CRT components stator and the rotors are modelled. At nozzle inlet, stagnation pressure boundary condition is used. At the turbine stage or rotor 2 outlet, mass flow rate is specified. Skin friction lines are drawn on rotor 1 as well as rotor 2 on all over the blade. Not much variation of skin friction lines is witnessed in rotor 1 on the pressure side with exception to the position of the separation line close to leading edge. On suction side, skin friction lines are more uniform when the speed ratio is greater than 1. Skin friction lines on rotor 2 pressure surface show the presence of re-attachment lines. The position of the nodal point of separation near the hub remained same, but the strength is decreasing with speed ratio. On rotor 2 suction side, near the tip, all along the stream wise direction, line of re-attachment is observed that spreads from leading edge to trailing edge, whose strength is varying with speed ratio. Near the hub as well, line of re-attachment is observed, which is of more intensity in lower speed ratios. For the same region in rotor 1, there is proper reattachment as nodes are observed instead of lines, suggesting that more improved flow is occurring in rotor 1 than rotor 2. Thus, the present paper identifies the flow modification with speed ratio in a counter rotating turbine. Also, effort is made to see the consequence of flow change on the output of CRT.

scholarly journals Leading-Edge Flow Sensing for Aerodynamic Parameter Estimation

AIAA Journal ◽  
2018 ◽  
Vol 56 (12) ◽  
pp. 4706-4718 ◽  
Author(s):  
Aditya Saini ◽  
Ashok Gopalarathnam
Keyword(s):  
Parameter Estimation ◽  
Leading Edge ◽  
Aerodynamic Parameter ◽  
Flow Sensing ◽  
Edge Flow
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