Aerodynamic characteristics of a wing-and-flap configuration in ground effect and yaw

Roberts, Luke S.; Correia, José Manuel; Finnis, Mark; Knowles, K.

doi:10.1177/0954407015596274

Cited by 16 publications

(16 citation statements)

References 24 publications

(61 reference statements)

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“…An asymmetric pressure distribution was present with one side of the wing producing more downforce than the other [16]. In the wake, all vortices formed by the lateral movement in the same direction as the mean flow were strengthened whilst those formed against the mean flow were weakened [16]. Under the cornering condition, downforce was reduced whilst drag increased [7].…”

Section: Introductionmentioning

confidence: 98%

“…Under the yaw condition, both drag and downforce reduced. This was attributed to a reduction in effective diffuser angle, loss of vortex enhancement and a change of stagnation locations [16]. An asymmetric pressure distribution was present with one side of the wing producing more downforce than the other [16].…”

Section: Introductionmentioning

confidence: 99%

“…This was attributed to a reduction in effective diffuser angle, loss of vortex enhancement and a change of stagnation locations [16]. An asymmetric pressure distribution was present with one side of the wing producing more downforce than the other [16]. In the wake, all vortices formed by the lateral movement in the same direction as the mean flow were strengthened whilst those formed against the mean flow were weakened [16].…”

Section: Introductionmentioning

confidence: 99%

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The Effect of Cornering on the Aerodynamics of a Multi-Element Wing in Ground Effect

Patel

Garmory

Passmore

2020

Fluids

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This research investigates the effects of cornering on a multi-element wing in ground effect with the aim to improve the understanding of such in the effort to improve the performance of open-wheel race cars. A numerical validation study was performed to confirm the validity of the Detached Eddy Simulation CFD methodology used. This involved comparing numerical data with wind tunnel experimental data using a force balance and PIV for the velocity field to reveal the trajectory of the trailing vortex system. Once validated, the CFD was used to test the wing within a cornering condition as well as fixed yaw condition and its aerodynamic performance relative to the straight-line condition was analysed. Asymmetry was the general theme concerning the on-surface pressure distribution with this most prominent under the cornering condition. Ultimately, minimal change was observed regarding the downforce generated whilst drag was found to increase in the cornering condition and decrease slightly in the fixed yaw condition. Asymmetry was also observed in the wake of the wing where alterations to the relative strengths of the vortices was observed as well as their downstream paths which was generally governed by the direction of the freestream flow.

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Section: Introductionmentioning

confidence: 98%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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The Effect of Cornering on the Aerodynamics of a Multi-Element Wing in Ground Effect

Patel

Garmory

Passmore

2020

Fluids

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“…The aerodynamic analysis of wings operating in ground effect has previously been conducted through both experimental and computational means . The computational studies [13][14][15][16][17][18][19][20][21][22][23] have, in general, used…”

Section: Introductionmentioning

confidence: 99%

Modelling boundary-layer transition on wings operating in ground effect at low Reynolds numbers

Roberts

Finnis

Knowles

2018

Proceedings of the Institution of Mechanical Engineers, Part D:

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The transition-sensitive, three-equation k- kL- ω eddy-viscosity closure model was used for simulations of three-dimensional, single-element and multi-element wing configurations operating in close proximity to the ground. The aim of the study was to understand whether the model correctly simulated the transitional phenomena that occurred in the low Reynolds number operating conditions and whether it offered an improvement over the classical fully turbulent k-ω shear stress transport model. This was accomplished by comparing the simulation results to experiments conducted in a 2.7 m × 1.7 m closed-return, three-quarter-open-jet wind tunnel. The model was capable of capturing the presence of a laminar separation bubble on the wing and predicted sectional forces and surface-flow structures generated by the wings in wind tunnel testing to within 2.5% in downforce and 4.1% in drag for a multi-element wing. It was found, however, that the model produced insufficient turbulent kinetic energy during shear-layer reattachment, predicted turbulent trailing-edge separation prematurely in areas of large adverse pressure gradients, and was found to be very sensitive to inlet turbulence quantities. Despite these deficiencies, the model gave results that were much closer to wind-tunnel tests than those given by the fully turbulent k-ω shear stress transport model, which tended to underestimate downforce. Significant differences between the transitional and fully turbulent models in terms of pressure field, wake thickness and turbulent kinetic energy production were found and highlighted the importance of using transitional models for wings operating at low Reynolds numbers in ground effect. The k- kL- ω model has been shown to be appropriate for the simulation of separation-induced transition on a three-dimensional wing operating in ground effect at low Reynolds number.

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“…The ground clearance and flow incidence angle of the aerodynamic devices such as front wing prove to particularly affect aerodynamic forces Roberts et al (2015). The front and rear parts of a car commonly have different ground clearances.…”

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confidence: 99%

Aerodynamic Forces Acting on a Race Car for Various Ground Clearances and Rake Angles

Džijan

Pašić

Buljac

et al. 2019

JAFM

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Computational model was developed to investigate aerodynamic forces acting on a closed-wheel race car. A particular focus was on the effects of ground clearance and rake angle on aerodynamic drag and lift forces. Computations were performed for a steady viscous fluid flow using the realizable k-ε turbulence model and non-equilibrium wall functions. The computational results indicate a strong influence of ground clearance and rake angle on aerodynamic loading of a race car. The largest drag force coefficient was obtained for the largest ground clearance. The drag force coefficient for the squatting car is larger by 5% compared to the reference case, where the both front and rear ground clearances are 100 mm. For the nose-diving car, the drag force coefficient is equal to the reference case. Increasing the ground clearance caused a negligible increase in the lift force coefficient in comparison with the reference case. A decrease in the ground clearance yielded an increase in the lift force coefficient. The largest positive lift force coefficient was obtained for a squatting car, whereas the largest negative lift force coefficient was observed for a nose-diving car. While the favorable aerodynamic downforce acting on front wheels is larger for a nose-diving car, for rear wheels it is larger for a squatting car.

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Aerodynamic characteristics of a wing-and-flap configuration in ground effect and yaw

Cited by 16 publications

References 24 publications

The Effect of Cornering on the Aerodynamics of a Multi-Element Wing in Ground Effect

The Effect of Cornering on the Aerodynamics of a Multi-Element Wing in Ground Effect

Modelling boundary-layer transition on wings operating in ground effect at low Reynolds numbers

Aerodynamic Forces Acting on a Race Car for Various Ground Clearances and Rake Angles

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