Turbulent flow around a wing-fuselage type juncture

Kubendran, L. R.; McMahon, Howard M.; Hubbartt, J.

doi:10.2514/6.1985-40

Cited by 12 publications

(12 citation statements)

References 5 publications

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“…In comparison with a similar experiment by Kubendran et al(1986), the Reynolds normal stresses at the core region show similar profiles, but the levels of the stress exhibited by the present experiment are higher. As Kubendran et al(1986) pointed out, the vortex strength was closely related to the slenderness ratio of the nose. The slenderness ratio of the nose is 1:1 in the present study, 1.5:1 in Kubendran et al(1986), and 6:1 in Shabaka(1979).…”

Section: Experimental Apparatus and Techniquessupporting

confidence: 55%

“…Shabaka(1979) made an experimental study of the decay process of the horseshoe vortex and the interaction between the two boundary layers in the corner of an idealized wing-body junction. Kubendran et al(1986) also presented the experimental results on turbulent flow around a wing-fuselage type junction. An uncambered wing of constant thickness downstream of a half-elliptic nose was used in both experiments.…”

Section: Introductionmentioning

confidence: 99%

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Behaviour of the Leg of the Horseshoe Vortex Around the Idealized Blade With Zero Attack Angle by Triple Hot-Wire Measurements

Honami

Shizawa

Takahama

1988

Volume 1: Turbomachinery

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The paper presents the flow measurements within the leg portion of the horseshoe vortex. An uncambered blade of constant thickness downstream with a half-circular nose of an idealized turbine blade was installed on a flat plate. The six components of the Reynolds stresses were measured in addition to the three mean velocity components at two cross-sectional planes by a triple wire probe. The predominant vortical motion of the secondary flow occurs at the corner of the blade and the endwall. The effect of the penetrative motion of the free-stream toward the corner region induced by the vortex on the Reynolds stress is found in u2 profiles near the blade, but not in v2 profiles. The diffusion of the Reynolds stresses is observed in the crossflow direction.

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Section: Experimental Apparatus and Techniquessupporting

confidence: 55%

Section: Introductionmentioning

confidence: 99%

Behaviour of the Leg of the Horseshoe Vortex Around the Idealized Blade With Zero Attack Angle by Triple Hot-Wire Measurements

Honami

Shizawa

Takahama

1988

Volume 1: Turbomachinery

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“…The vast majority of this research involves cylinders (circular or streamlined) mounted normal to a flat plate, and usually aligned with the streamwise direction (0~ Mehta (1984) and Shin (1989) studied the effects of appendage nose shape on the generation of streamwise vorticity and the resulting horseshoe vortex mean flow structure. Kubendran et al (1986) documented the mean vortex path, and noted some similarities between the turbulent shear stresses and the mean flow strain rates for the flow around a constant thickness body with a 3:2 elliptic nose. Shabaka and Bradshaw's (1981) measurements revealed that the eddy viscosities for the -fi-~ and -fi-ff Reynolds stresses are anisotropic and are negative over large regions in a wing-body junction.…”

Section: Introductionmentioning

confidence: 99%

An experimental study of a turbulent wing-body junction and wake flow

Fleming

Simpson

Cowling

et al. 1993

Experiments in Fluids

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Extensive measurements were conducted in an incom-X v pressible turbulent flow around the wing-body junction formed by Y a 3:2 semi-elliptic nose/NACA 0020 tail section and a fiat plate.Y + Mean and fluctuating velocity measurements were performed adja-Z cent to the wing and up to 11.56 chord lengths downstream. The 6 appendage far wake region was subjected to an adverse pressure 6" gradient. The authors' results show that the characteristic horseshoe 0 vortex flow structure is elliptically shaped, with 0 (W)/OY forming # the primary component of the streamwise vorticity. The streamwise 0 development of the flow distortions and vorticity distributions is Zw highly dependent on the geometry-induced pressure gradients and f2 x resulting flow skewing directions.The primary goal of this research was to determine the effects of Subscript the approach boundary layer characteristics on the junction flow.TC To accomplish this goal, the authors' results were compared to several other junction flow data sets obtained using the same body shape. The trailing vortex leg flow structure was found to scale on T. A parameter known as the momentum deficit factor (MDF = (ReT) 2 (O/T)) was found to correlate the observed trends in mean flow distortion magnitudes and vorticity distribution. Changes in 6IT were seen to affect the distribution of u', with lower ratios producing well defined local turbulence maxima. Increased thinning of the boundary layer near the appendage was also observed for small values of 6/T.

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“…Khan and Ahmed [26] determined that the effect of the wing sweep on the flow structure is significant as the forward swept wing has a lower turbulence kinetic energy level. Kubendran et al [30] found that the slenderness ratio of the wing leading edge affects the location and the strength of the vortex that wraps around the wing.…”

Section: Subsonic Flowmentioning

confidence: 99%

Numerical prediction of the interference drag of a streamlined strut intersecting a surface in transonic flow

Tetrault

2000

38th Aerospace Sciences Meeting and Exhibit

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In transonic flow, the aerodynamic interference that occurs on a strut-braced wing airplane, pylons, and other applications is significant. The purpose of this work is to provide relationships to estimate the interference drag of wing-strut, wing-pylon, and wing-body ar- his office, leaving with more answers than questions. I also appreciate the fact that he has always had a friendly attitude towards me. I have enjoyed interacting with Dr. Kapania, whose cheerful attitude and perpective on life and research is very similar to mine. I would like to acknowledge the contribution of Dr. Grossman to the team in the field of numerical calculations and his desire of improving the life of the graduate students by forming the Graduate Advisory Committee. Dr. Raj deserves a lot of thanks for providing me with useful advice throughout this project despite his busy schedule. I appreciate the fact that he has always been interested in knowing more about the evolution of my research work and career. The "virtual" presence of Dr. Haftka during our weekly meetings has been very beneficial because of his ability to foresee difficulties and to get the team members to not lose sight of the big picture.

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Turbulent flow around a wing-fuselage type juncture

Cited by 12 publications

References 5 publications

Behaviour of the Leg of the Horseshoe Vortex Around the Idealized Blade With Zero Attack Angle by Triple Hot-Wire Measurements

Behaviour of the Leg of the Horseshoe Vortex Around the Idealized Blade With Zero Attack Angle by Triple Hot-Wire Measurements

An experimental study of a turbulent wing-body junction and wake flow

Numerical prediction of the interference drag of a streamlined strut intersecting a surface in transonic flow

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