Aerodynamic design optimization of a helicopter rotor blade-sleeve fairing

Pölzlbauer, Patrick; Desvigne, Damien; Breitsamter, Christian

doi:10.1007/s13272-018-0341-0

Cited by 5 publications

(8 citation statements)

References 9 publications

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“…The tool chain contains several commercial as well as non-commercial software packages and a detailed description is provided in Ref. 10…”

Section: Optimisation Approachmentioning

confidence: 99%

“…Moreover, the minimisation of drag is Figure 4. Optimisation tool chain allowing for automated shape development (10) .…”

Section: Optimisation Problemmentioning

confidence: 99%

“…The shape variation of the BSF is achieved by replacing the supporting aerofoils. For this purpose, a database of selected 2D geometries is employed, which was generated during previous work within the FURADO project ( 10 ) . The four supporting aerofoils (S 1 –S 4 ) are located in a region of , where R corresponds to the rotor radius.

Figure 2.CAD model applied for the design optimisation of the RACER blade-sleeve fairing (baseline design).…”

Section: Geometry Parameterisationmentioning

confidence: 99%

“…The tool chain contains several commercial as well as non-commercial software packages and a detailed description is provided in Ref. 10.

Figure 4.Optimisation tool chain allowing for automated shape development ( 10 ) .…”

Section: Optimisation Approachmentioning

confidence: 99%

“…2 is examined. During preliminary work, the supporting aerofoils (S 1 –S 4 ) were aerodynamically optimised for cruise flight, which is the most relevant flight condition in terms of drag reduction ( 10 ) . For this purpose, the local flow conditions for each section were taken into account, which vary due to the circumferential velocity of the rotor and the flow deflection caused by the fuselage.…”

Section: Optimisation Approachmentioning

confidence: 99%

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Performance improvement of a compound helicopter rotor head by aerodynamic design optimisation of a blade-sleeve fairing

2019

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Within the present publication, the rotor head of a compound helicopter known as Rapid And Cost-Effective Rotorcraft (RACER) is investigated. In particular, the aerodynamic design optimisation of the RACER blade-sleeve fairings (BSFs) is conducted. For this purpose, an isolated rotor head is generated featuring a full-fairing beanie, the BSF and a truncated rotor blade (RB). Moreover, a single RB is investigated at two different azimuthal rotor positions, which correspond to the advancing and the retreating RB case. For this purpose, an averaged circumferential velocity is determined in the blade-sleeve region and superposed with the RACER cruise speed in order to estimate the prevailing flow conditions. The automated aerodynamic design optimisation is performed by means of a previously developed optimisation tool chain. A global multi-objective genetic optimisation algorithm is applied for the given problem. During preliminary work, a 2D aerodynamic design optimisation of selected blade-sleeve sections was conducted. These optimised aerofoils represent the design variables for the current optimisation problem. The shape modification of the 3D fairing is realised by exchanging specific aerofoils at certain spanwise sections.

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“…The tool chain contains several commercial as well as non-commercial software packages and a detailed description is provided in Ref. 10…”

Section: Optimisation Approachmentioning

confidence: 99%

“…Moreover, the minimisation of drag is Figure 4. Optimisation tool chain allowing for automated shape development (10) .…”

Section: Optimisation Problemmentioning

confidence: 99%

Figure 2.CAD model applied for the design optimisation of the RACER blade-sleeve fairing (baseline design).…”

Section: Geometry Parameterisationmentioning

confidence: 99%

“…The tool chain contains several commercial as well as non-commercial software packages and a detailed description is provided in Ref. 10.

Figure 4.Optimisation tool chain allowing for automated shape development ( 10 ) .…”

Section: Optimisation Approachmentioning

confidence: 99%

Section: Optimisation Approachmentioning

confidence: 99%

See 3 more Smart Citations

Performance improvement of a compound helicopter rotor head by aerodynamic design optimisation of a blade-sleeve fairing

2019

Self Cite

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Propeller Blade Shape Optimization with a Hybrid BEMT/CFD Approach

Kümmel

Stuhlpfarrer

Pölzlbauer

et al. 2019

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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Vortex Identification and Quantification on Blunt Trailing-Edge Rotor Blades in Reverse Flow

Wild

Jones

2023

AIAA Journal

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An inherent aerodynamic limitation of high-advance-ratio high-speed helicopters is reverse flow on the retreating blades, which can be a source of several unsteady effects, like vortex formation, that reduce rotor performance. The current study is the first detailed comparison of a rotor with a conventional, sharp trailing-edge NACA 0012 airfoil section with one equipped with a blunt-edge elliptical airfoil section. The aim was to detect and quantify vortex formation in reverse flow using planar particle image velocimetry on a subscale, low-Reynolds-number rotor rig in a water tank. The investigated blade azimuth angles ranged from 240 to 300 deg for advance ratios between 0.40 and 1.00 at pitch angles from 13 to 25 deg. Four main vortex structures were detected. At the aerodynamic leading edge, a strong interference of the tip vortex with the reverse-flow dynamic stall vortex was identified when blade flapping was restricted. Dynamic stall vortices advect closer to the blade surface for the blunt elliptical airfoil, thus reducing the wake area in reverse flow. Blade pitch kinematics govern the reverse-flow entrance-vortex strength and coherency. A coherent vortex street or wake sheet forms at the aerodynamic trailing edge of either airfoil. Overall, the vortex structures that form on the ellipse are more coherent than those on the NACA 0012. The current study highlights the significance of airfoil geometry, specifically the trailing-edge curvature, of an airfoil on the resulting vortex structures in reverse flow, strongly affecting the rotor performance at high advance ratios.

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Aerodynamic design optimization of a helicopter rotor blade-sleeve fairing

Cited by 5 publications

References 9 publications

Performance improvement of a compound helicopter rotor head by aerodynamic design optimisation of a blade-sleeve fairing

Performance improvement of a compound helicopter rotor head by aerodynamic design optimisation of a blade-sleeve fairing

Propeller Blade Shape Optimization with a Hybrid BEMT/CFD Approach

Vortex Identification and Quantification on Blunt Trailing-Edge Rotor Blades in Reverse Flow

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