Wing Download Results from a Test of a 0.658-Scale &lt;I&gt;V&lt;/I&gt;-22 Rotor and Wing

Felker, Fort F.

doi:10.4050/jahs.37.58

Cited by 22 publications

(21 citation statements)

References 5 publications

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“…Aerodynamically, previous studies mainly focus on tiltrotor wing performance in the helicopter mode, including both the hovering and forward flight regimes. Tests about the aerodynamic characteristics of a 0.658-scale V-22 model in hover were performed in the Ames Research Center [5].…”

Section: Introductionmentioning

confidence: 99%

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Numerical Simulation of Rotor–Wing Transient Interaction for a Tiltrotor in the Transition Mode

Cao

2019

Mathematics

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Tiltrotor aerodynamic interaction, especially in the transition mode, is a necessary consideration for tiltrotor aerodynamics, and structural design and optimization. Previous studies have paid much attention to the helicopter mode. However, due to the substantial complexity of the problem, only a small amount of work on the transition mode has been done so far. In this paper, the rotor–wing aerodynamic interaction of a scaled V-22 Osprey tiltrotor, both in the helicopter and transition modes, are studied by computational fluid dynamics (CFD) numerical simulation. The flow field is discretized via the chimera mesh technique and then solved with the Reynolds-averaged Navier–Stokes (RANS) equations. The rotational acceleration of the rotor is considered as a source term added on the right side of the momentum equation of the RANS equations. Both a quasi-steady and a fully transient method are employed to simulate the tilt motion of the rotor in the transition mode. Both qualitative and quantitative results are presented and discussed on the aerodynamic forces, flow physics, and mechanisms. The applicability of the extensively used quasi-steady method for rotor tilt simulation is revealed.

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Section: Introductionmentioning

confidence: 99%

“…Due to the symmetry of the model, only half of the model is simulated. The geometrical characteristics and dimensions are reported in Table 1 (more details can be obtained from Felker [5]).…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Rotor–Wing Transient Interaction for a Tiltrotor in the Transition Mode

Cao

2019

Mathematics

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“…[16]. Good data repeatability and reduced interference effects of the outdoor testing apparatus make this a high-quality dataset for computational validation.…”

Section: Isolated Rotor Test Casesmentioning

confidence: 99%

CFD Simulations of Tiltrotor Configurations in Hover

Potsdam¹,

Strawn²

2005

j am helicopter soc

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Navier-Stokes computational fluid dynamics calculations are presented for isolated, half-span, and full-span V-22 tiltrotor hover configurations. These computational results extend the validity of CFD hover methodology beyond conventional rotorcraft applications to tiltrotor configurations. Computed steady-state, isolated rotor perfomiance agrees well with experimental measurements, showing little sensitivity to grid resolution. However, blade-vortex interaction flowfield details are sensitive to numerical dissipation and are more difficult to model accurately. Time-dependent, dynamic, half-and full-span installed configurations show sensitivities in performance to the tiltrotor fountain flow. As such, the full-span configuration exhibits higher rotor performance and lower a h m e download than the half-span configuration. Half-span rotor installation trends match available half-span data, and airframe downloads are reasonably well predicted. Overall, the CFD solutions provide a wealth of flowfield details that can be used to analyze and improve tiltrotor aerodynamic performance.

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“…International Journal of Aerospace Engineering [26] is given in Figure 11. Very good agreement between the calculated results and the measurements is observed.…”

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confidence: 99%

Numerical Calculations on the Unsteady Aerodynamic Force of the Tilt-Rotor Aircraft in Conversion Mode

Chen

2019

International Journal of Aerospace Engineering

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A computational method is developed in order to predict the unsteady aerodynamic characteristics of the tilt-rotor aircraft in conversion mode. In this approach, the rotor is modeled as an actuator disk so that the effect of individual blades can be ignored. A novel predictor-corrector-based dynamic mesh method is presented for dealing with extremely large mesh deformation during a conversion process. The dual time-stepping approach and the finite volume scheme are applied to solve the unsteady N-S equation. A parallel algorithm is utilized in this work to improve the computational efficiency. By using the present method, quantitative and qualitative comparisons are made between the aerodynamic coefficients obtained in the quasi-steady fixed conversion mode and the time-accurate continuous transition flight condition. Both two-dimensional (2D) and three-dimensional (3D) computations are carried out. The influence of the tilt modes and the tilt period time on the unsteady aerodynamic forces are also studied. Numerical results demonstrate that the developed method is effective in simulating the aerodynamic characteristics of the tilt-rotor aircraft in conversion mode.

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Wing Download Results from a Test of a 0.658-Scale <I>V</I>-22 Rotor and Wing

Cited by 22 publications

References 5 publications

Numerical Simulation of Rotor–Wing Transient Interaction for a Tiltrotor in the Transition Mode

Numerical Simulation of Rotor–Wing Transient Interaction for a Tiltrotor in the Transition Mode

CFD Simulations of Tiltrotor Configurations in Hover

Numerical Calculations on the Unsteady Aerodynamic Force of the Tilt-Rotor Aircraft in Conversion Mode

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