Single Blade Computations of Helicopter Rotors in Forward Flight

Biava, Massimo; Bindolino, Giampiero; Vigevano, Luigi

doi:10.2514/6.2003-52

Cited by 8 publications

(7 citation statements)

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“…Figure 19 shows the predicted chordwise pressure distribution on the blade surface at the radial position 0.82R. As can be seen, the calculated pressures from the coupling method are in close agreement with the experimental data at three azimuthal angles, except at 90°, where the pressure is overestimated (Biava et al, 2003). This discrepancy could arise from the integrated vorticity source approach, which induces the smaller velocity at the blade tip region.…”

Section: Low-speed Flight Casesupporting

confidence: 62%

“…The comparisons between the predicted time-history of sectional normal force with the experimental data (Biava et al, 2003) at two radial positions are shown in Figure 20. Because of the well-preserved tip vortex in the coupling method, the multiple BVI events -which occurred at the outerboard of the blade at 90°and 270°-resulted in oscillations of sectional lift at these locations.…”

Section: Low-speed Flight Casementioning

confidence: 99%

“…In this section a low-speed case of the Helishape 7A rotor (Biava, Bindolino, & Vigevano, 2003) was used to demonstrate the reliability of the coupling method in the forward flight case. The four-bladed 7A rotor is articulated with a radius of R = 2.1 m, aspect ratio of 15, and solidity σ = 0.0849.…”

Section: Low-speed Flight Casementioning

confidence: 99%

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Rotor wake and flow analysis using a coupled Eulerian–Lagrangian method

Shi

Peng

2016

Engineering Applications of Computational Fluid Mechanics

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A coupled Eulerian-Lagrangian methodology was developed in this paper in order to provide an efficient and accurate tool for rotor wake and flow prediction. A Eulerian-based Reynolds-averaged Navier-Stokes (RANS) solver was employed to simulate the grid-covered near-body zone, and a gridfree Lagrangian-based viscous wake method (VWM) was implemented to model the complicated rotor-wake dynamics in the off-body wake zone. A carefully designed coupling strategy was developed to pass the flow variables between two solvers. A sample case of a forward flying rotor was performed first in order to show the capabilities of the VWM for wake simulations. Next, the coupled method was applied to rotors in several representative flight conditions. Excellent agreement regarding wake geometry, chordwise pressure distribution and sectional normal force with available experimental data demonstrated the validity of the method. In addition, a comparison with the full computational fluid dynamics (CFD) method is presented to illustrate the efficiency and accuracy of the proposed coupled method. ARTICLE HISTORY

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Section: Low-speed Flight Casesupporting

confidence: 62%

Section: Low-speed Flight Casementioning

confidence: 99%

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Rotor wake and flow analysis using a coupled Eulerian–Lagrangian method

Shi

Peng

2016

Engineering Applications of Computational Fluid Mechanics

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“…Despite grid refinement, high order-accuracy schemes and adaptive grids can be used to reduce numerical dissipation, but these methods are still insufficient at capturing the wake structure entirely; furthermore, vast amounts of computation time and resources limit their applications in researching the rotor BVI problem. In recent years, a coupled method combining the wake model with the Euler solver was developed [14][15][16][17] and several remarkable studies on BVI noise have been reported in [18,19] demonstrating the capability of the coupled method to predict BVI noise; however, the wake solutions rely on empirical formulations due to the assumption of inviscid flow, resulting in some errors regarding BVI airload prediction.…”

Section: Aerodynamic Modelmentioning

confidence: 99%

“…Compared with the results in Figure 6, the miss-distance increases with a tilted forward angle. We see in Equation (14) that the amplitude of BVI noise depends on the interaction airload and its time derivative, thus the impacts on the sectional airload at 0.9 R are illustrated in Figure 10. As shown, with the rotor disk tilted forward, the impulse load amplitude decreases and the impulse characteristics become weaker due to the increase in the miss-distance.…”

Section: Sensitivity Study Of Bvi Noisementioning

confidence: 99%

Helicopter Blade-Vortex Interaction Airload and Noise Prediction Using Coupling CFD/VWM Method

Zhao

Shi

2017

Applied Sciences

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As a high resolution airload with accurate rotor wake is pivotal for rotor BVI (Blade-vortex interaction) analysis, a hybrid method with combined Navier-Stokes equation, viscous wake model, and FW-H (Ffowcs Williams-Hawkings) equation is developed for BVI airload and noise in this paper. A comparison with the CFD (Computational Fluid Dynamics)/FW-H method for the AH-1/OLS (Operational Load Survey) rotor demonstrates its capability for favorable accuracy and high computation efficiency. This paper further discusses the mechanisms for the impacts of four flight parameters (i.e., tip-path-plane angle, thrust coefficient, tip Mach number, advance ratio) on BVI noise. Under the BVI condition, several BVI events concurrently occur on the rotor disk. Each interaction has a distinct radiation direction which depends on the interaction azimuth, and its noise intensity is highly associated with the characteristic parameters (e.g., miss-distance, interaction angle, vortex strength). The BVI noise is dominated by the interactions at 30-90 • in azimuth on the advancing side, of which the wake angle range is from 180 • to 540 • . Furthermore, the tip-path-plane angle, thrust coefficient, and tip Mach number change the noise intensity mainly via miss-distance, interaction angle, and vortex strength, but for different advance ratios, the noise intensity and propagation direction are more dependent on the interaction angle and interaction azimuth.

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Numerical Research on the Unsteady Evolution Characteristics of Blade Tip Vortex for Helicopter Rotor in Forward Flight

Zhou

Zhan

2020

Int. J. Aeronaut. Space Sci.

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Single Blade Computations of Helicopter Rotors in Forward Flight

Cited by 8 publications

References 0 publications

Rotor wake and flow analysis using a coupled Eulerian–Lagrangian method

Rotor wake and flow analysis using a coupled Eulerian–Lagrangian method

Helicopter Blade-Vortex Interaction Airload and Noise Prediction Using Coupling CFD/VWM Method

Numerical Research on the Unsteady Evolution Characteristics of Blade Tip Vortex for Helicopter Rotor in Forward Flight

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