The influence of V/STOL vehicle configuration variables on vectored jet induced flow fields in ground effect

Author(s):  
D. KOTANSKY
1993 ◽  
Author(s):  
G. SCHIPHOLT ◽  
N. VOOGT ◽  
J. VAN HENGST
Keyword(s):  

2014 ◽  
Vol 11 (98) ◽  
pp. 20140505 ◽  
Author(s):  
Erica J. Kim ◽  
Marta Wolf ◽  
Victor Manuel Ortega-Jimenez ◽  
Stanley H. Cheng ◽  
Robert Dudley

Aerodynamic performance and energetic savings for flight in ground effect are theoretically maximized during hovering, but have never been directly measured for flying animals. We evaluated flight kinematics, metabolic rates and induced flow velocities for Anna's hummingbirds hovering at heights (relative to wing length R = 5.5 cm) of 0.7 R , 0.9 R , 1.1 R , 1.7 R , 2.2 R and 8 R above a solid surface. Flight at heights less than or equal to 1.1 R resulted in significant reductions in the body angle, tail angle, anatomical stroke plane angle, wake-induced velocity, and mechanical and metabolic power expenditures when compared with flight at the control height of 8 R . By contrast, stroke plane angle relative to horizontal, wingbeat amplitude and wingbeat frequency were unexpectedly independent of height from ground. Qualitative smoke visualizations suggest that each wing generates a vortex ring during both down- and upstroke. These rings expand upon reaching the ground and present a complex turbulent interaction below the bird's body. Nonetheless, hovering near surfaces results in substantial energetic benefits for hummingbirds, and by inference for all volant taxa that either feed at flowers or otherwise fly close to plant or other surfaces.


2015 ◽  
pp. 791-797 ◽  
Author(s):  
I García-Hermosa ◽  
J Brossard ◽  
Z Cohen ◽  
G Perret ◽  
G Pinon ◽  
...  

Author(s):  
Berend G. van der Wall ◽  
Jianping Yin

A simple analytical real-time capable model to account for fuselage-induced velocities at rotor blade elements is described at the example of the Bo105 fuselage. Data of the fuselage-induced flow fields in the volume of rotor operation above the fuselage are first computed by a panel method in the range of angle of attack and sideslip of [Formula: see text]. The model parameters are then estimated based on these data. The usefulness of the model in combinations of angle of attack and sideslip is demonstrated.


1997 ◽  
Vol 119 (2) ◽  
pp. 354-359 ◽  
Author(s):  
Tienfuan Kerh ◽  
J. J. Lee ◽  
L. C. Wellford

Numerical investigation on the interaction of a viscous incompressible fluid with a control valve is conducted by using the finite element method and Newmark approach. Variables including displacement, velocity, and acceleration are presented as a function of time to describe movements of the solid system. The velocity vectors, pressure variations, pressure loss coefficients, and energy losses are displayed to reveal the resulting flow fields. It is observed that the motion of the structural element which becomes a moving boundary had a significant influence on the flow fields. In a periodic inlet flow, the motion of the structural system and the resulting flow fields were almost identical for each cycle after the third cycle. The simulated results presented in this paper provide a good description of the induced flow field in a piping system under the effect of a pulsating piston or a wave.


Author(s):  
Sertac Cadirci ◽  
Hasan Gunes ◽  
Ulrich Rist

A Jet and Vortex Actuator (JaVA) is an oscillatory, zero-net-mass flux active flow control device which has been investigated numerically in quiescent water. JaVA consists of a vertically moving actuating plate and ejects jets or vortices into the quiescent fluid. Main JaVA-induced flow regimes include jets to different orientations and vortex mode. In this paper, we investigate the effect of the wide gap on the flow characteristics. Three cases consisting of two jets and one vortex mode are presented in detail where the jet-Reynolds number and the scaled amplitude are kept constant. Computational results have been reported to depict instantaneous fields and reveal temporal behavior of JaVA-induced flows in quiescent fluid. In addition, the phase-averaged flow fields have been obtained for suction and blowing phases. The velocity profiles extracted from phase-averaged flow fields across the wide gap supply further insight into the JaVA-induced flow regime and their effectiveness in flow control.


2021 ◽  
Vol 33 (2) ◽  
pp. 339-347
Author(s):  
Yasutada Tanabe ◽  
Hideaki Sugawara ◽  
Shigeru Sunada ◽  
Koichi Yonezawa ◽  
Hiroshi Tokutake ◽  
...  

A variable-pitch-controlled quadrotor drone was simulated in the ground effect using a high-fidelity CFD solver. In contrast to a single rotor in the ground effect, which has been extensively studied for conventional helicopters, the flow fields around multiple rotors are complex. In this study, the rotating speed of the rotors was maintained constant, and the blade pitch angles were adjusted so that the total thrust of the multicopter was the same regardless of the rotor height from the ground. It was observed that the power required for the quadrotors, which generate the same thrust, decreases when the rotors are approaching the ground from the height where they can be considered to be out of the ground effect, but increases locally when the rotor height is approximately the rotor radius, owing to flow recirculation into the rotor, and then decreases abruptly when the rotors further approach the ground. The outwash from the quadrotors depends heavily on the direction relative to the quadrotor layout. Along the plane crossing the diagonal rotor centers, the outwash velocity profiles resemble those of a single rotor; however, the outwash from the rotor gaps is stronger and extends to a much higher altitude.


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