Flowfield Analysis of Modern Helicopter Rotors in Hover by Navier‐Stokes Method

Srinivasan, G. R.; Raghavan, Venugopalan S. G.; Duque, Earl P. N.; Mccroskey, W. J.

doi:10.4050/jahs.38.3.3

Cited by 51 publications

(11 citation statements)

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“…The computational domain was constructed around one blade for efficient computation, and periodic boundary condition was applied. For the far boundaries, the source-sink model was adopted to prescribe the rotor outflow below the blade by the 1-D momentum theory that was proposed by Srinivasan et al [11].…”

Section: Numerical Method: Helinamentioning

confidence: 99%

Effect of the Blade Inner-Tip Position on the Generation of Twin Vortices

Jung

Choi

Lee

2008

Journal of Aircraft

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Engineering Notes ENGINEERING NOTES are short manuscripts describing new developments or important results of a preliminary nature. These Notes should not exceed 2500 words (where a figure or table counts as 200 words). Following informal review by the Editors, they may be published within a few months of the date of receipt. Style requirements are the same as for regular contributions (see inside back cover).

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Section: Numerical Method: Helinamentioning

confidence: 99%

Effect of the Blade Inner-Tip Position on the Generation of Twin Vortices

Jung

Choi

Lee

2008

Journal of Aircraft

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“…One of the earliest first principles CFD using NS was performed by Srinivasan and his co-workers (Refs. [57][58][59]. Subsequent refinements to the first principles approach can be divided into two categories, one based on finer grids in vortical flow regions and the other based on higher order discretization schemes.…”

Section: Three-dimensional Airloads and Wakementioning

confidence: 99%

Review of Rotor Loads Prediction with the Emergence of Rotorcraft CFD

Datta¹,

Nixon²,

Chopra³

2007

J. Am. Helicopter Society

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This paper reviews the state of the art in helicopter rotor loads prediction with the emergence of computational fluid dynamics (CFD) and computational structural dynamics (CSD) coupling. The focus is on steady level flight, where most of the current CFD/CSD analyses are being applied. The application of CFD to rotorcraft problems has evolved, over the period 1990-2005, as a viable means to improve the aerodynamic modeling used in rotorcraft comprehensive analyses (CA). It has the potential to meet the ultimate objective of a coupled rotor-fuselage analysis that can predict loads and vibration accurately at all critical flight conditions without semi-empirical inputs. The paper begins by identifying three critical level flight conditions. These are useful to isolate the key aerodynamic and structural dynamic mechanisms. It is followed by a review of the capabilities and limitations of current CFD analyses in representing the key aerodynamic mechanisms: threedimensional airloads and wake, dynamic stall, unsteady transonic effects near the tip, and fuselage aerodynamic effects. The structural dynamic methods are then briefly reviewed. Finally, the recent rotorcraft CFD/CSD coupling methods are described and evaluated on the basis of their loads prediction capability. The emphasis is on the fundamental aeroelastic mechanisms which determine the critical rotor loads, and with which the accuracy and efficiency of all CFD/CSD coupled analyses should be assessed. Nomenclature

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“…The BERP planform is known to have superior performance compared to other blade designs at high speed forward-flight and high blade loading, while hover performance compared to for example, a planform with a parabolic blade tip is similar. Since the development of this rotor [11] and with the exception of some works [12], [13], [14] not much validation has been performed for BERP blades. Optimisation of BERP-like tip geometries were performed by Johnson and Barakos [15], but the final shape was not tested in a wind tunnel.…”

Section: Introductionmentioning

confidence: 99%