Bubble Bursting and Stall Hysteresis on Single-Slotted Flap High-Lift Configuration

Baragona, Marco; Boermans, Loek; Tooren, M.J.L. Van; Bijl, H.; Beukers, Adriaan

doi:10.2514/2.2091

Cited by 5 publications

(5 citation statements)

References 11 publications

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“…Fuselage: we employ the fuselage geometry of NASA's trapezoidal wing configuration used in the first AIAA CFD high-lift prediction workshop [37] and utilize computeraided design data, which the workshop released on the website. 1…”

Section: Configurationmentioning

confidence: 99%

“…There are three principal types of high-lift systems: the flap mechanism, the boundary-layer control mechanism, and B Kazuhisa Chiba kazchiba@uec.ac.jp 1 The University of Electro-Communications, 1-5-1, Chofugaoka, Chofu, Tokyo 182-8585, Japan 2 Japan Aerospace Exploration Agency, 7-44-1, Jindaiji-higashi, Chofu, Tokyo 182-8522, Japan the turbulence utilization mechanism [5]. Estimating the aerodynamic performance of high-lift systems is still a challenge in airplane design due to the complexity of the fluid phenomenon [41].…”

Section: Introductionmentioning

confidence: 99%

“…A typical HLD used in modern commercial airplanes is a slotted flap [44], which forms a gap between a wing and a flap [1]. This mechanism has all the effects of a trailing-edge flap.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Aerodynamic efficacy of adding yaw-wise rotational degree of freedom to an airplane flap

Chiba

Komatsu

Ito

2020

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This study scrutinized the aerodynamic change of adding a yaw-wise rotational degree of freedom to a single slotted flap of airplane via computational fluid dynamic analyses. Existing slotted flaps have spanwise constant gaps and are disharmonious with the 3D nature of the flow field. A flap geometry and its angle condition are sensitive to aerodynamic performance; small variations in them must be useful in aerodynamic improvement. To add the yaw-wise rotation to a flap is a lower hurdle than to attain other high-lift systems. Therefore, after defining a simple configuration consisting of a fuselage, a wing, and a single slotted flap, we investigated the mesh dependency to consider the diversity in flow phenomena precisely; we examined the effect of the yaw-wise rotation for the flap on improving the whole lift. To place the flap at suitable yaw-wise rotation angles consequently effected raising the lift. We revealed the physical mechanism that accelerating the fluid in the gap between the wing and the flap changes the separation structure on the flap upper surface and grows the lift.

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Section: Configurationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Aerodynamic efficacy of adding yaw-wise rotational degree of freedom to an airplane flap

Chiba

Komatsu

Ito

2020

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“…The transition between positions on the curve can lead to a sharp loss of lift, and to prevent stall, a rapid change in the angle of attack is necessary. This was the reason for a detailed study of the occurrence and prevention of this phenomenon [1][2][3].…”

Section: Introductionmentioning

confidence: 99%

Numerical Study of the Influence of the Critical Reynolds Number on the Aerodynamic Characteristics of the Wing Airfoil

Utkina,

Kozelkov,

Zhuchkov

et al. 2023

Fluids

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The paper reports the results of a study concerned with the influence of the size of the leading edge laminar bubble on the aerodynamic characteristics of the HGR01 airfoil. The completely turbulent and transient flows are considered. The mechanism of the appearance and interaction of laminar and turbulent flow separation near the leading and trailing edges of the airfoil is studied in detail. In the paper, the dependence of aerodynamic forces on the critical Reynolds number for the HGR01 airfoil is discussed. It has been established that the separation bubble at the leading edge can only be obtained using the laminar–turbulent transition model. Fully turbulent models are not able to show this feature of the airfoil flow. Graphs of the lift coefficient as a function of the critical Reynolds number, as well as the pressure distribution as a function of the size of the laminar bubble, are shown.

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“…Determination of the transition position is handled either by databases of solutions of the Orr-Sommerfeld differential equation or by envelope-methods derived from such databases. Also semi-empirical approaches are used to determine the bubble size [17] and burst [2]. The prediction of transition on a laminar separation bubble is new in the context of flow solvers based on the Reynolds-averaged Navier-Stokes equations (RANS).…”

Section: Introductionmentioning

confidence: 99%

RANS Simulation and Experiments on the Stall Behaviour of a Tailplane Airfoil

Wokoeck

Grote

Krimmelbein

et al. 2006

New Results in Numerical and Experimental Fluid Mechanics V

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Measurements and simulations are presented of the flow past a tailplane research airfoil which is designed to show a mixed leading-edge trailing-edge stall behaviour. The numerical simulations were carried out with two flow solvers that introduce transition prediction based on linear stability theory to RANS simulations for cases involving laminar separation bubbles. One of the methods computes transition locations across laminar separation bubbles whereas the other assumes transition onset where laminar separations occur. For validation of the numerical methods an extensive measurement campaign has been carried out. It is shown, that the methodology mentioned first can simulate the size of laminar separation bubbles for angles of attack up to where the separation bubble and the turbulent separation at the trailing edge are well behaved and steady in the mean. With trailing edge separation involved, the success of the new numerical procedure relies on the diligent choice of a turbulence model. Finally, for flows with increased unsteady behaviour of both, separation bubble and turbulent separation, which were observed at higher angles of attack in the experiment between maximum lift and leading-edge stall, steady state prediction methods for transition can no longer be applied and time-accurate methods have to be developed in a further step.

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Bubble Bursting and Stall Hysteresis on Single-Slotted Flap High-Lift Configuration

Cited by 5 publications

References 11 publications

Aerodynamic efficacy of adding yaw-wise rotational degree of freedom to an airplane flap

Aerodynamic efficacy of adding yaw-wise rotational degree of freedom to an airplane flap

Numerical Study of the Influence of the Critical Reynolds Number on the Aerodynamic Characteristics of the Wing Airfoil

RANS Simulation and Experiments on the Stall Behaviour of a Tailplane Airfoil

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