Numerical study of the aerodynamics of a NACA 4412 airfoil in dynamic ground effect

Qu, Qiulin; Jia, Xiaoyun; Wang, Wei; Liu, Peiqing; Agarwal, Ramesh K.

doi:10.1016/j.ast.2014.07.016

Cited by 46 publications

(19 citation statements)

References 11 publications

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“…7). For the ride height of h/c = 0.1, the pressure coefficient on the lower surface in DGE is larger than one, especially for the main wing and flap, in which the compression work [17,18] plays an important role. Compared with a single-element airfoil, the compression work of a multi-element airfoil is relatively weaker in DGE because of the air leakage from the gaps between the elements.…”

Section: Dge Resultsmentioning

confidence: 98%

Numerical Study of Aerodynamics and Flow Physics of the 30P30N Three-Element Airfoil in Dynamic Ground Effect

Wang

Agarwal

Huang

et al. 2016

34th AIAA Applied Aerodynamics Conference

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The ground effect aerodynamics of high lift devices is very important for the safe take-off and landing of large aircrafts. The flow fields around the 30P30N three-element airfoil in static ground effect (SGE) and dynamic ground effect (DGE) are simulated by solving the Reynolds Averaged Navier-Stokes equations and the Spalart-Allmaras turbulence model. The relative motion between the airfoil and the ground in DGE is dealt with by the dynamic laying mesh technology. The lift in SGE and DGE decreases with the reduction in ride height.For large ride heights, the lift in DGE is the same as the value in the SGE with the same angle of attack (AOA). For small ride heights, the lift in DGE is larger than that in the SGE with the same AOA, which is due to additional pressure increment on the lower surface resulting from the compression work. The flow velocity in the gaps of 30P30N in DGE is bigger than that in SGE with the same AOA, which is due to the larger pressure difference between the lower and supper surfaces as a result of the compression work. Nomenclature c = chord length of the clean airfoil C p = pressure coefficient C L = lift coefficient h = ride height, i.e. the distance from the trailing edge of the airfoil to the ground l = local coordinate in the gap Ma = Mach number Re = Reynolds number based on the clean airfoil chord U = local velocity U ∞ = free stream velocity U v = airfoil sinking velocity α = angle of attack (AOA) γ = flight path angle θ = pitch angle ΔC L = the increment of lift coefficient

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Section: Dge Resultsmentioning

confidence: 98%

Numerical Study of Aerodynamics and Flow Physics of the 30P30N Three-Element Airfoil in Dynamic Ground Effect

Wang

Agarwal

Huang

et al. 2016

34th AIAA Applied Aerodynamics Conference

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“…Beberapa riset tentang karakteristik aerodinamika NACA 4412 di antaranya eksperimen Ahmed dkk [9] yang meneliti efek ground pada airfoil, serta dua simulasi numerik airfoil yang mempertimbangkan efek dynamic ground oleh Qu dkk [10] dan sebelumnya bentuk airfoil dengan flap pada efek extreme ground [11]. Hasil penelitian menunjukkan pentingnya aspek "ground effect" yang mempengaruhi karakteristik aerodinamika airfoil.…”

Section: Pendahuluanunclassified

Studi Eksperimental dan Simulasi Numerik Karakteristik Aerodinamika Airfoil NACA 4412

Effendy

Muchlisin

2019

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The objective of this study is to investigate the aerodynamics characteristic of airfoil NACA 4412 based on experiment and numerical simulation. A 3D airfoil with chord length (C) of 100 mm and span-width (S) of 200 mm was fabricated in order to be tested by subsonic wind tunnel at inlet air velocity of 10 m/s, whereas numerical study was realised by 2D airfoil reffering to geometrics in the experiment. The structured mesh with 810,000 elements number was constructed by Gambit meshing tools up to reach the near wall resolution of Δy+ = 17.2. Spallart-Almaras turbulence model was applied in the simulation of RANS study.The effect of various angle of attack (α) between -5 and 20 was investigated for both methods in terms of the aerodinamic characteristics such as lift coefficient (CL), drag coefficient (CD), and lift-drag ratio (L/D). The pressure coefficient (CP) and flow visualisations around the airfoil were generated by simulation method. In general, the results show that the data resulted by both methods agree well compared to the other studies, mainly for the lift and drag coefficients. Both coefficients increase with rising the angle of attack before approaching a stall condition at α = 15 o . From this point, lift coefficient drops significantly due to large turbulent wake that reduces to lift and influence to drag. The change of attack angles influences the shifting of both stagnation and expansion points in the leading edge, furthermore it causes the overall aerodynamic characteristics. The increase of pressure difference between upper and lower surfaces of airfoil body causes the rise of lift.

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“…The research papers on static ground effect include both the two-dimensional (2-D) chorddominated ground effect and the three-dimensional (3-D) spandominated ground effect [1,4]. Qu et al [8] systematically studied the ground effect of a NACA 4412 airfoil.…”

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confidence: 99%

“…Both studies indicated that the lift in dynamic ground effect is larger than that in static ground effect, and the difference becomes larger with the increasing sink rate. Qu et al [4,5] simulated the landing process of a NACA 4412 airfoil using the finite-volume method. They also found that the lift in dynamic ground effect is larger than that in the static ground effect; they introduced the compression work concept to explain the lift enhancement phenomenon in dynamic ground effect.…”

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confidence: 99%

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Numerical Investigation of the Aerodynamics of an Airfoil in Mutational Ground Effect

Zuo

Wang

et al. 2015

AIAA Journal

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distance between the trailing edge of the airfoil and the top of the platform) L = x value of the side wall of the platform in the Cartesian coordinates p ∞ = static pressure at outlet boundaries Re = Reynolds number based on chord length u = velocity component in the x direction V ∞ = freestream velocity V = flight velocity of airfoil x, y = Cartesian coordinates with the origin located at the leading edge of the airfoil α = angle of attack β = velocity vector angle (i.e., angle between velocity vector and the positive direction of x axis) Δt = time step ΔC L R = dimensionless lift coefficient increment δ f = deflection angle of flap δ s = deflection angle of slat λ = aspect ratio Subscripts low = lower surface of airfoil t1, t2 = time up = upper surface of airfoil

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Numerical study of the aerodynamics of a NACA 4412 airfoil in dynamic ground effect

Cited by 46 publications

References 11 publications

Numerical Study of Aerodynamics and Flow Physics of the 30P30N Three-Element Airfoil in Dynamic Ground Effect

Numerical Study of Aerodynamics and Flow Physics of the 30P30N Three-Element Airfoil in Dynamic Ground Effect

Studi Eksperimental dan Simulasi Numerik Karakteristik Aerodinamika Airfoil NACA 4412

Numerical Investigation of the Aerodynamics of an Airfoil in Mutational Ground Effect

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