Wing/canard interference of a close-coupled canard configuration in static ground effect

Qin, Ying-zhi; Liu, Peiqing; Qu, Qiulin; Hu, Tianxiang

doi:10.1016/j.ast.2017.06.012

Cited by 17 publications

(4 citation statements)

References 23 publications

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“…Many of these numerical computations have been approved by the wind and water tunnels tests. 9-12 According to the results, the vortex breakdown over the wing in presence of canard occurs farther from the wing trailing edge than that for an isolated wing.…”

Section: Introductionmentioning

confidence: 93%

Effects of canard oscillations on the unsteady flowfield over the wing in supersonic flow

Davari

Soltani

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Few studies have been devoted to effects of canard oscillations on the flowfield over the wing in supersonic flow and the associated time lags. In this article, an in-depth experimental study on a closely coupled canard-wing-body configuration in supersonic flow has been undertaken to mark the zone of influence of the oscillatory canard on the wing. Surface pressure measurements have been performed on the wing downstream of canard in both static and oscillatory cases at various wing angles of attack and canard deflection angles as well as the canard oscillation amplitudes and frequencies. The results show that the upwash and downwash flowfields due to an oscillatory canard periodically change the effective angle of attack seen by the wing and have different effects on various regions. In supersonic flow, the pressure rise due to the oblique shock waves causes the primary flow separation and the vortex break down onsets to occur at higher angles of attack, comparing to those in the lower speed regimes. According to the results, the mid-span region on the wing, which is directly in the shadow of the oscillating canard, receives more disturbances. During upstroke, the canard induces a downwash field to the front half of the wing, while in downstroke motion, the front regions of the wing experience upwash flow, giving rise to the effective angle of attack seen by the wing. Among various oscillation parameters, the pitching amplitude was observed to have a strong impact on the time lag in flowfield over the wing.

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Section: Introductionmentioning

confidence: 93%

Effects of canard oscillations on the unsteady flowfield over the wing in supersonic flow

Davari

Soltani

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…It was discovered that increasing the angle of attack in the ground effect amplified the blockage effect while reducing the nose-up pitching moment. The Delayed Detached Eddy Simulation and Spalart-Allmaras turbulence model were used to investigate the aerodynamics and flow physics of a close-coupled canard configuration with a sharp leading edge in static ground effect (Qin et al, 2017), as well as a 65 °sweep delta wing with a sharp leading edge in both static and dynamic ground effect (Qin et al, 2015;Qin et al, 2016).…”

Section: Frontiers In Mechanical Engineeringmentioning

confidence: 99%

Aerodynamic characteristics of a delta wing aircraft under ground effect

Shams Taleghani,

Ghajar

2024

Front. Mech. Eng.

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The main objective of this study is to investigate the impact of ground effects on the aerodynamic coefficients of a delta wing aircraft model. Since the flow on the delta wing exhibits vortical flow inherently, it is crucial to examine the influence of ground effects under these conditions. An experimental study was conducted to enhance understanding of the aerodynamic behavior of an aircraft model incorporating a delta wing-body-vertical tail. Experiments were conducted in a subsonic wind tunnel with a test section measuring 2.8 m × 2.2 m. Measurements were taken using a sting type balance to determine the aerodynamic forces and moments. All experimental tests were performed at a Reynolds number of 1.5 × 106, with the specific aim of examining and identifying the influence of the ground on aerodynamic coefficients. To investigate how ground effect affects the aerodynamic performance of the model, a fixed plate with an adjustable height was placed underneath it. The distance between the model and the ground was varied, and resulting data indicated that increased proximity to the ground improved longitudinal static stability. The results revealed that the presence of the ground plane resulted in a 6% increase in the maximum lift coefficient. Meanwhile, the lift increases around 25% due to ground effects at an angle of attack of 14° as it approaches the ground. The lift coefficient was enhanced across all angles of attack, while the induced drag coefficient decreased, resulting in an overall increase in aerodynamic efficiency. The lift curve slope saw a 16.9% increase when the model’s height from the ground plane was less than half of the wing span. As the height decreased further, the aerodynamic center shifted backward, leading to an increase in longitudinal static stability. The rolling moment and yawing moment coefficients becomes unstable at angles of attack above 30°.

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“…Dakhrabadi 17 , et al studied ground effect characteristics as well as stability of compound wing. Qin 18 , et al analysed the ground effect of canard configuration numerically. They reported that non-linear increment in lift, drag as well as nose-down pitching moment coefficients with reduction in ground clearance.…”

Section: Introductionmentioning

confidence: 99%

Prediction of Moment Using a Modified Discrete Vortex Method in Ground Effect

Mondal

2021

Def. Sc. J.

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The aerodynamics around a wing is modified when it comes near the ground. This is generally referred to as ground effect. In this work, a discrete vortex method based model which can predict two-dimensional (2D) ground effect from its free flight data is proposed. The required data in free flight could be generated either from high fidelity CFD solver or experiments. In this method, strength of the vortex distribution as obtained from discrete vortex based method is modified using a constrained optimisation procedure to match the free flight aerodynamic data. This vortex distribution is further modified due the presence of the ground. The efficacy of present model is demonstrated for predicting the moment of multi element airfoils in ground effect. The predicted aerodynamic coefficient in ground effect compares well with high fidelity CFD data.

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Wing/canard interference of a close-coupled canard configuration in static ground effect

Cited by 17 publications

References 23 publications

Effects of canard oscillations on the unsteady flowfield over the wing in supersonic flow

Effects of canard oscillations on the unsteady flowfield over the wing in supersonic flow

Aerodynamic characteristics of a delta wing aircraft under ground effect

Prediction of Moment Using a Modified Discrete Vortex Method in Ground Effect

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