Aerodynamic Loads Induced by a Rotor on a Body of Revolution

Smith, Charles A.; Betzina, Mark D.

doi:10.4050/jahs.31.1.29

Cited by 18 publications

(1 citation statement)

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“…This led to closer understanding of the interaction mechanisms and to improving the prediction capability of complete helicopter configurations. The studies can be categorized as purely experimental or experimental-cum-theoretical work [4][5][6][7][8][9][10], simple analytical or numerical work that uses simplified aerodynamic and structural models [11][12][13][14][15][16][17][18][19][20], and computationally more involved work that directly solves Euler or Navier-Stokes equations for the rotorcraft flow field [21][22][23][24][25][26][27].…”

Section: Introduction and Objectivesmentioning

confidence: 99%

Semi-empirical modeling of fuselage–rotor interference for comprehensive codes: the fundamental model

et al. 2014

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The flow field around the isolated HART II fuselage is computed by a computational fluid dynamics code. Velocities normal to the rotor rotational plane are extracted in a volume around the rotor as a data basis. A simple semi-empirical analytical formulation of the fuselage-induced velocities, based on parameter identification from computational fluid dynamics or measured data, is developed for use in comprehensive rotor codes. This model allows the computation of fuselage-rotor interferences on the rotor blade element level. It also allows the prediction of the rotor wake geometry deformation due to the presence of the fuselage in both prescribed wake and free-wake codes. Its impact on rotor thrust, power and trim is evaluated analytically using blade element momentum theory and by DLR's comprehensive rotor code.

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Section: Introduction and Objectivesmentioning

confidence: 99%

Semi-empirical modeling of fuselage–rotor interference for comprehensive codes: the fundamental model

et al. 2014

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Semi-empirical modeling of fuselage–rotor interference for comprehensive codes: influence of side-slip angle

Wall

Yin

2016

CEAS Aeronaut J

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A semi-empirical and physics-based analytical formulation of the induced velocities generated by the fuselage shell of the Bo105 wind tunnel model in the volume around the rotor is derived from velocity data computed by a panel code. The reduced-order analytical model is several orders of magnitude faster than the panel code and thus is predestinated for use in comprehensive rotor codes. Angle of attacks investigated include vertical descent, shallow descent, level flight and climb to vertical ascent. Side-slip angles range from forward to quartering flight. The analytical induced velocity model can be directly used to account for the inflow at the blade elements and also allows for analytical or numerical integration of rotor wake convection to compute the associated displacements of rotor blade tip vortices travelling downstream within this velocity field. This model will be used to replace a fully panelized fuselage (and thus significantly reduce the computational effort) throughout a simulation with an aeromechanics code to account for the influence of the fuselage (e.g., in a design stage). The usage within an aerodynamics code (e.g., a panel code) reduces the panelization to the rotor blades only, leaving the computation of the fuselage-induced velocities to the model. The focus of this paper is the analytical evaluation of fuselagerotor interference in side-slip angles on rotor trim controls, using blade element momentum theory. The results are compared to the influence of thrust-induced inflow gradients on rotor trim.

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GAMMA2D: A multiregion/multiblock, structured/unstructured grid generation package for computational mechanics

Huang

Oden

1994

Computers & Structures

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Aerodynamic Loads Induced by a Rotor on a Body of Revolution

Cited by 18 publications

References 0 publications

Semi-empirical modeling of fuselage–rotor interference for comprehensive codes: the fundamental model

Semi-empirical modeling of fuselage–rotor interference for comprehensive codes: the fundamental model

Semi-empirical modeling of fuselage–rotor interference for comprehensive codes: influence of side-slip angle

GAMMA2D: A multiregion/multiblock, structured/unstructured grid generation package for computational mechanics

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