A numerical investigation on flow past skewed vortex generators ahead of a backward facing ramp

Cheawchan, A.; Mohamed, M.A.; Ng, Bing Feng; New, T. H.

doi:10.1016/j.ast.2022.107435

Cited by 6 publications

(2 citation statements)

References 44 publications

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“…Reducing flow separation and recirculation in this simplified model holds significant implications for industrial flow applications. The potential of passive devices such as vortex generators [41][42][43] and active devices such as microjet actuators [44][45][46][47][48][49] to the effective ramp separation control have been successfully demonstrated in the state-ofthe-art experiments and numerical simulations. The current research adopts a smooth backward-facing ramp profile initially proposed in [40].…”

Section: Separation Control On a Smooth Ramp Using Hybrid Passive And...mentioning

confidence: 99%

Enhancing Flow Separation Control Using Hybrid Passive and Active Actuators in a Matrix Configuration

Li,

Zhang

2024

Aerospace

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Efficient control of flow separation holds significant economic promise. This study investigates flow separation mitigation using an experimental platform featuring a combination of passive and active actuators arranged in a matrix configuration. The platform consists of 5 × 6 hybrid actuator units, each integrating a height-adjustable vortex generator and a micro-jet actuator. Inspired by the distributed pattern of V-shaped scales on shark skin, these actuator units are strategically deployed in a matrix configuration to reduce flow separation on a backward-facing ramp. Distributed pressure taps encircling the hybrid actuators monitor the flow state. Parametric analyses examine the effect of different control strategies. By adopting appropriate passive and active actuation patterns, effective pressure recovery on the ramp surface can be achieved. The most significant flow control outcome occurs when the actuators operate under combined active and passive excitation, harnessing the benefits of both control strategies. Particle image velocimetry (PIV) results confirm a notable reduction in flow separation under the best-controlled case. These findings suggest a promising future for flow control devices employing combined passive and active actuation in matrix-like configurations.

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Section: Separation Control On a Smooth Ramp Using Hybrid Passive And...mentioning

confidence: 99%

Enhancing Flow Separation Control Using Hybrid Passive and Active Actuators in a Matrix Configuration

Li,

Zhang

2024

Aerospace

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“…Based on the procedure outlined by [25], a minimum of three grids of increasing fineness, with a recommended grid refinement factor (l coarse /l f ine ) of approximately 1.3, are required to estimate the GCI. This methodology has been used for reporting the uncertainty of numerical simulation results for various aerodynamic phenomena such as vortex shedding of flapping wings [26], flow separation [27], and wing-propeller interaction [28].…”

Section: Numerical Simulationsmentioning

confidence: 99%

Flow Structures and Aerodynamic Behavior of a Small-Scale Joined-Wing Aerial Vehicle under Subsonic Conditions

New

Teo

et al. 2023

Aerospace

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Flow behavior and aerodynamic performance of a small-scale joined-wing unmanned aerial vehicle (UAV) was studied experimentally and numerically under various pitch and yaw angle combinations in subsonic flow conditions. Selected numerical results are compared against experimental results obtained using surface oil flow visualizations and force measurements, with additional simulations expanding the range of combined pitch and yaw configurations. Under zero-yaw conditions, increasing the pitch angle leads to the formation of symmetric ogive vortex roll-ups close to the fuselage and their significant interactions with the fore-wing. Additionally, contributions to lift and drag coefficients under zero-yaw conditions by the key UAV components have been documented in detail. In contrast, when the UAV is subjected to combined pitch and yaw, no clear evidence of such ogive vortex roll-ups can be observed. Instead, asymmetric flow separations occur over the fuselage’s port side and resemble bluff-body flow behavior. Additionally, these flow separations become more complex, and they interact more with the fuselage and fore- and aft-wings when the yaw angle increases. Lift and drag variations due to different pitch and yaw angle combinations are also documented. Finally, rolling and yawing moment results suggest that the present UAV possesses adequate flight stability unless the pitch and yaw angles are high.

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Influences of microjet pressure and number of microjets on the control of shock wave/boundary layer interaction

Huang

et al. 2023

Aerospace Science and Technology

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A numerical investigation on flow past skewed vortex generators ahead of a backward facing ramp

Cited by 6 publications

References 44 publications

Enhancing Flow Separation Control Using Hybrid Passive and Active Actuators in a Matrix Configuration

Enhancing Flow Separation Control Using Hybrid Passive and Active Actuators in a Matrix Configuration

Flow Structures and Aerodynamic Behavior of a Small-Scale Joined-Wing Aerial Vehicle under Subsonic Conditions

Influences of microjet pressure and number of microjets on the control of shock wave/boundary layer interaction

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