Numerical Simulation of Flow around Rigid Rotor in Forward Flight

Абалакин, И. В.; Bobkov, V. G.; Kozubskaya, T. K.; Vershkov, V. A.; Kritsky, B. S.; Mirgazov, R. M.

doi:10.1134/s0015462820040011

Cited by 11 publications

(4 citation statements)

References 14 publications

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“…8 also presents the contours of the gauge pressure distribution the rotor surface. The detailed problem setup and results analysis presented in the [15].…”

Section: Rigid Rotor In Forward Flight Modementioning

confidence: 99%

Simulation of Helicopter Rotors On Unstructured Mixed Meshes Using Edge-Based Reconstruction Schemes

Bobkov¹,

Abalikin²,

Kozubskaya³

2021

14th WCCM-ECCOMAS Congress

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The paper gives a detailed description of the developed numerical method for simulating the turbulent flow around a helicopter rotor and calculating its aerodynamic characteristics. The method is based on the original vertex-centered finite-volume EBR schemes. The features of these schemes are their higher accuracy that is achieved through the use of edge-based reconstruction of variables on extended quasi-one-dimensional stencils, and a moderate computational cost that allows for serial computations. When dealing with discontinuities or solutions with large gradients, a quasi-one-dimensional EBR-WENO scheme is used. The methods are implemented in the in-house code NOISEtte within the hybrid MPI-OpenMP parallel model. Validation of the developed techniques is carried out by simulating several cases for hovering and forward-flight regimes of helicopter rotors.

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“…8 also presents the contours of the gauge pressure distribution the rotor surface. The detailed problem setup and results analysis presented in the [15].…”

Section: Rigid Rotor In Forward Flight Modementioning

confidence: 99%

Simulation of Helicopter Rotors On Unstructured Mixed Meshes Using Edge-Based Reconstruction Schemes

Bobkov¹,

Abalikin²,

Kozubskaya³

2021

14th WCCM-ECCOMAS Congress

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“…53 Rotating frame motion has been applied in CFD work by early researchers. [54][55][56][57] The same strategy is recommended by Ansys ® for the simulations of rotating objects like analysis of helicopter rotor blades, propellers, fan blades and vortex interaction from helicopters rotor.…”

Section: Validation Of Pure Pitch Motion Using Unsteady Mesh Motionmentioning

confidence: 99%

Numerical estimation of longitudinal damping derivatives of a flying wing micro aerial vehicle

Shams

Shah

Shahzad

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Longitudinal damping derivatives, [Formula: see text], of an aerial vehicle is important from an aerodynamic stability point of view. Experimental calculation of longitudinal damping derivatives using wind tunnel is not a cost-effective method; therefore, researchers have developed numerical solutions as an alternative. In this research, the longitudinal damping derivatives of a flying wing micro aerial vehicle (FWMAV) were calculated using numerical simulations by adopting pull-up maneuver and forced harmonic motion in pitch axis. Pull-up maneuver with four steady rotational rates was simulated to obtain pitch rate derivative, C mq. Combined derivative, [Formula: see text], was obtained by simulating forced harmonic motion of FWMAV around a mean angle of attack of 0° with amplitude of oscillation of ± 3° using four reduced frequencies (0.02, 0.03, 0.04, and 0.05). Unstructured surface and volume mesh was used in a spherical domain engulfed inside a large cuboid domain for moving reference frame strategy. Reynolds number taking mean aerodynamic chord as a reference length was 2.33 × 105. Spalart–Allmaras turbulence model was used. Pitch rate derivative, combined derivative, and acceleration derivative were found as − 0.03/rad, − 7.39/rad, and − 7.36/rad, respectively, by the use of a phase method at a reduced frequency of 0.03. During flight dynamic analysis, it was found that [Formula: see text] has a significant contribution on damping in short period mode with no effect on Phugoid mode. The research concluded that for tailless configurations, acceleration derivative [Formula: see text] can exist and can provide necessary damping in the longitudinal flight mode.

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“…In this research, different combination of supercritical airfoil in the helicopter rotor blades is used to delay the onset of shock wave and to increase the Critical Mach number. The Helicopters have complex aerodynamic features like advancing and retreating sides of blades during rotation [7]. In the advancing side, the leading edge faces the flow direction whereas in the retreating side, the trailing edge faces the flow direction [8].…”

Section: Introductionmentioning

confidence: 99%

Forward Flight Performance Analysis of Supercritical Airfoil in Helicopter Main Rotor

Hasan¹,

Mukesh²,

Krishnan³

et al. 2022

Intelligent Automation &Amp; Soft Computing

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In this research, the aerodynamic performance and flow characteristics of NASA SC (2)-0714 airfoil and HH02 airfoil in the helicopter main rotor are evidently analyzed. The supercritical airfoil is used in the aircraft for attaining better transonic and high-speed flow characteristics. Moreover, a specialized helicopter airfoil called HH02 is used in the Apache helicopter rotor for increasing the operational speed. As most of the high-speed helicopters are using four-bladed main rotor configuration, it is analyzed with prior attention. The lift and thrust act in different directions for the forward phase of the flight whereas the lift and thrust act in the same direction for the other phases of flight, which is analyzed in this work. The computational analysis is done by using ANSYS Fluent whereas the rotational analysis is done by using the Multiple Reference Frame (MRF) method. An analysis is carried out for different RPM of 400,600 and 800 with the combination of 0.3, 0.4 and 0.5 Mach numbers with the assistance of grid independence test. The result shows that the NASA SC (2)-0714 rotor increases the thrust of the rotor around 5% to 10% under various rotor and forward speeds. Thus, the results proves that the supercritical airfoil is highly capable of producing higher thrust and good aerodynamic characteristics.

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Numerical Simulation of Flow around Rigid Rotor in Forward Flight

Cited by 11 publications

References 14 publications

Simulation of Helicopter Rotors On Unstructured Mixed Meshes Using Edge-Based Reconstruction Schemes

Simulation of Helicopter Rotors On Unstructured Mixed Meshes Using Edge-Based Reconstruction Schemes

Numerical estimation of longitudinal damping derivatives of a flying wing micro aerial vehicle

Forward Flight Performance Analysis of Supercritical Airfoil in Helicopter Main Rotor

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