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(6)
Empirical Validation
incompressible navierstokes equation
Length Scale
Reynolds Number
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GENERALIZED VISCOUS VORTEX MODEL FOR APPLICATION TO FREEVORTEX WAKE AND AEROACOUSTIC CALCULATIONS
GENERALIZED VISCOUS VORTEX MODEL FOR APPLICATION TO FREEVORTEX WAKE AND AEROACOUSTIC CALCULATIONS,Mahendra J. Bhagwat,J. Gordon Leishman
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GENERALIZED VISCOUS VORTEX MODEL FOR APPLICATION TO FREEVORTEX WAKE AND AEROACOUSTIC CALCULATIONS
(
Citations: 3
)
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Mahendra J. Bhagwat
,
J. Gordon Leishman
The development of a generalized viscous vortex model is described for application in rotor aeroacoustic analyses. A brief summary is given of previous models for the viscous core growth and induced
velocity field
of a trailing tip vor tex. The assumptions made for the vortex core growth are shown to influence the predictions of the rotor wake ge ometry, as well as the induced velocities, airloads, and performance, thereby emphasizing the need for a more universal and physically representative vortex model. In the present approach, the viscous core growth was mod eled using an extension of the classic LambOseen model for the diffusion of laminar vortices. Turbulence in the tip vortex affects the diffusion of vorticity, and these effects were incorporated using an empirically validated correc tion for the average apparent or "eddy" viscosity. The vortex induced velocity profiles measured in experiments were found to exhibit strong selfsimilarity when using the vortex core radius as a lengthscale, suggesting that a gen eralized model is possible. A family of algebraic models for the swirl, axial, and radial components of the veloc ity induced by a viscous trailing tip vortex is proposed. These velocity components were found from a solution to a simplified form of the incompressible NavierStokes equations. The velocity profiles are written in terms of a single integer exponent with the viscous core growth be ing given by a semiempirical relation for the turbulent viscosity that scales as a function of the vortex Reynolds number. The model is compared with
velocity field
mea surements for both fixedwing and rotatingwing tip vor tices, with good agreement.
Published in 2002.
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Citation Context
(3)
...Notice that the Lamb‐Oseen model approaches the Burnham‐ Hallockmodelforsmall ,andboth modelsapproachthemodel obtained through Biot‐Savart’s law for large [
37
]...
Federico S. Cattivelli
,
et al.
Modeling Bird Flight Formations Using Diffusion Adaptation
...An initial vortex based on Scully vortex model [
9
] is used with circulation of 0.2536 and core radius of 0.162 to agree with the measurement [3]...
Yasutada Tanabe
,
et al.
A Parametric Study on Parallel BladeVortex Interaction for Helicopter...
...The disadvantage of this model is: it underestimates the maximum swirl velocity, see Leishman & Bhagwat [
5
]...
Yasser Aboelkassem
,
et al.
Viscous dissipation of Rankine vortex profile in zero meridional flow
References
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(
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)
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Challenges in Understanding the Vortex Dynamics of Helicopter Rotor Wakes
(
Citations: 24
)
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,
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Journal:
Aiaa Journal  AIAA J
, vol. 36, no. 7, pp. 11301140, 1998
Wake Model for Helicopter Rotors in High Speed Flight
(
Citations: 3
)
W. R. Johnson
Published in 1988.
A mathematical model illustrating the theory of turbulence
(
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)
J. M. Burgers
Computation of Helicopter Rotor Wake Geometry and Its Influence on Rotor Harmonic Airloads
(
Citations: 11
)
M. Scully
Published in 1975.
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Citations
(3)
Modeling Bird Flight Formations Using Diffusion Adaptation
(
Citations: 1
)
Federico S. Cattivelli
,
Ali H. Sayed
Journal:
IEEE Transactions on Signal Processing  TSP
, vol. 59, no. 5, pp. 20382051, 2011
A Parametric Study on Parallel BladeVortex Interaction for Helicopter Rotor
Yasutada Tanabe
,
Shigeru Saito
,
Keisuke Takasaki
,
Hajime Fujita
Published in 2007.
Viscous dissipation of Rankine vortex profile in zero meridional flow
(
Citations: 3
)
Yasser Aboelkassem
,
Georgios H. Vatistas
,
Nabil Esmail
Journal:
Acta Mechanica Sinica  ACTA MECH SINICA
, vol. 21, no. 6, pp. 550556, 2006