Numerical Simulations on the PSP Rotor Using HMB3

Jiménez-García, Antonio; Barakos, George N.

doi:10.2514/6.2018-0306

Cited by 2 publications

(1 citation statement)

References 18 publications

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“…The taper and sweep closely match the HVAB blade tip. The PSP rotor results in hover matched the experimental results as published by Jimenez-Garcia and Barakos [13] and Fitzgibbon et al [14], with the latter work comparing fixed and free transition results, and explaining in more detail the PSP blade results in level flight. The PSP rotor is very close to the HVAB planform, described in Section IV.…”

Section: Introductionsupporting

confidence: 85%

Numerical Analysis of HVAB and STAR Rotor Blades Using HMB3

Steininger

Barakos

Woodgate

2023

AIAA SCITECH 2023 Forum

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Computational Fluid Dynamics simulations of the Hover Validation and Acoustic Baseline, Smart Twisting Active Rotor, and Active Twist Rotor blades in hover are presented. For these blades, the effect of twist in hover is examined, using the in-house simulation tools of Glasgow University. Rigid and aeroelastic methods are also compared for these rotors. In forward flight, high-twist may be associated with increased blade vibration. For the Smart Twisting Active Rotor blades, the effect of static twist and of a 2/rev harmonic active twist input are also investigated at a high advance forward ratio flight conditions. A vibration index is used to quantify the harmonic components of hub forces and moments. The hover simulations were computed on grids of 10-16m cells, coupled with structural updates. The results show the strong effect of blade twist on hover performance. The forward flight cases were computed on a 36m cell grid and using a modal aeroelastic method.

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Section: Introductionsupporting

confidence: 85%

Numerical Analysis of HVAB and STAR Rotor Blades Using HMB3

Steininger

Barakos

Woodgate

2023

AIAA SCITECH 2023 Forum

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Experimental investigation of vortex core properties of a finite span wing and an isolated rotor model

Stepanov

Kusyumov

Pakhov

et al. 2021

J. Phys.: Conf. Ser.

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This work outlines results of an experimental investigation of vortex core properties of a finite span wing and a helicopter rotor model operating at hover mode. Experimental data was obtained using Stereo-PIV in T1-K wind tunnel at KNRTU-KAI named after A.N. Tupolev. An empirically derived formula is proposed, allowing to estimate the dependence of the vortex core size from the threshold Q-value. The wing tip vortices were measured for different angles of attack. The tip vortices from the rotor blades were measured at two collective pitch angles. The results indicate that the obtained empirical equation can be used to estimate the impact of the lowest threshold Q-value selection on the size of the vortex core, which facilitates a more objective approach compared to known methods, when used to eliminate non-essential vortical regions.

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Numerical Simulations on the PSP Rotor Using HMB3

Abstract: = blade loading coefficient, thrust coefficient divided by rotor solidity

Cited by 2 publications

References 18 publications

Numerical Analysis of HVAB and STAR Rotor Blades Using HMB3

Numerical Analysis of HVAB and STAR Rotor Blades Using HMB3

Experimental investigation of vortex core properties of a finite span wing and an isolated rotor model

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