Computational Investigations on the Effects of Gurney Flap on Airfoil Aerodynamics

Jain, Shubham; Sitaram, N.; Krishnaswamy, Sriram

doi:10.1155/2015/402358

Cited by 32 publications

(25 citation statements)

References 19 publications

(26 reference statements)

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“…A larger deflection of the exit flow at the trailing edge is pushed toward the GF, which also causes an increase in the effective downwash and, then, the work capability of the fan. Similar results are also reported in studies conducted by Jain et al 32 In order to illustrate the static pressure variation with the GFs, the static pressure distribution on the suction surface is presented in Figure 12. There are two obvious high-pressure zones on the suction surface of the baseline fan.…”

Section: Flow Analysis Of a Fan With Gfsupporting

confidence: 82%

Experimental and numerical study on the performance of an axial fan with a Gurney flap

Chen

Xie

et al. 2018

Advances in Mechanical Engineering

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Gurney flap is a miniature lift-enhancement device installed at the airfoil trailing edge and has been successfully applied to fixed wing aircraft and low-speed horizontal wind turbines. In this article, Gurney flap is extended to increase pressure output of a diffusive cascade flow in rotating turbomachinery, which is complicated for its three dimensionalities and diffusive separation characteristics. Wind tunnel tests and computational fluid dynamic simulations were accomplished on an axial fan profiled with an NACA 65-(12)10 airfoil to investigate the effects of Gurney flap on the performance of a high solidity. We present the detailed flow features of the fan with and without Gurney flap after validating the simulation results with the experimental datum. The experimental results show positive Gurney flap effects on fan's pressure rise and flow rate improvement. However, negative Gurney flap effects on fan's efficiency are more evident than Gurney flap on isolated airfoils. Detailed flow field analysis from computational fluid dynamic computation reveals that the increased airfoil pressure loading along the fan blade chord strengthens the tip leakage flow, which induces more tip second flow losses than in the baseline fan. In addition to the positive lift enhancement, the net Gurney flap effect in diffusion cascade is influenced by the three-dimensional flow structure.

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Section: Flow Analysis Of a Fan With Gfsupporting

confidence: 82%

Experimental and numerical study on the performance of an axial fan with a Gurney flap

Chen

Xie

et al. 2018

Advances in Mechanical Engineering

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“…The attacking angle of the airfoils were set to zero since we only interested in studying the effect of gurney flap on various incoming airspeeds. Similar study with a different type of NACA airfoil has been done by Ref [5,6].…”

Section: Methodssupporting

confidence: 57%

Simulating the Aerodynamics Profiles of NACA 4312 Airfoil in Various Incoming Airspeed and Gurney Flap Angle

Sumaryada

Jaya

Kartono

2018

Omega J. Phys. Phys. Educ.

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“…Previous studies show that out of two equation RANS based models of FLUENT, -RNG model is best suited for the present airfoil study [12,13]. However these computations are carried out at a higher Reynolds number of 2.1 × 10 6 .…”

Section: Turbulence Modelingmentioning

confidence: 99%

Effect of Reynolds Number on Aerodynamics of Airfoil with Gurney Flap

Jain

Sitaram

Krishnaswamy

2015

International Journal of Rotating Machinery

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Steady state, two-dimensional computational investigations performed on NACA 0012 airfoil to analyze the effect of variation in Reynolds number on the aerodynamics of the airfoil without and with a Gurney flap of height of 3% chord are presented in this paper. RANS based one-equation Spalart-Allmaras model is used for the computations. Both lift and drag coefficients increase with Gurney flap compared to those without Gurney flap at all Reynolds numbers at all angles of attack. The zero lift angle of attack seems to become more negative as Reynolds number increases due to effective increase of the airfoil camber. However the stall angle of attack decreased by 2° for the airfoil with Gurney flap. Lift coefficient decreases rapidly and drag coefficient increases rapidly when Reynolds number is decreased below critical range. This occurs due to change in flow pattern near Gurney flap at low Reynolds numbers.

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Computational Investigations on the Effects of Gurney Flap on Airfoil Aerodynamics

Cited by 32 publications

References 19 publications

Experimental and numerical study on the performance of an axial fan with a Gurney flap

Experimental and numerical study on the performance of an axial fan with a Gurney flap

Simulating the Aerodynamics Profiles of NACA 4312 Airfoil in Various Incoming Airspeed and Gurney Flap Angle

Effect of Reynolds Number on Aerodynamics of Airfoil with Gurney Flap

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