Formation Flight of Low-Aspect-Ratio Wings at Low Reynolds Number

Korkischko, Ivan; Konrath, Robert

doi:10.2514/1.c033941

Cited by 10 publications

(4 citation statements)

References 26 publications

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“…Wagner et al [16] confirmed increased savings of 17.5% for the second wingman compared to first which yielded 15% savings [17]. Recently, Ivan and Roberts [18] conducted wing tunnel tests using multiple wings configurations with each wing having low aspect ratio of two; a total power savings of 14% and 24% in two and three wings configurations was obtained. In correspondence to finding an optimum spacing between the various units in formation, numerous studies also shed light on effect of leader's shape and size on the follower [19,20].…”

Section: Introductionmentioning

confidence: 97%

A Multi-Fidelity Approach for Aerodynamic Performance Computations of Formation Flight

et al. 2018

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This paper introduces a multi-fidelity computational framework for the analysis of aerodynamic performance of flight formation. The Vortex Lattice and Reynolds Averaged Navier-Stokes methods form the basis of the framework, as low-and high-fidelity, respectively. Initially, the computational framework is validated for an isolated wing, and then two rectangular NACA23012 wings are considered for assessing the aerodynamic performance of this formation; the optimal relative position is through the multi-fidelity framework based on the total drag reduction. The performance estimates are in good agreement with experimental measurements of the same configuration. Total aerodynamic performance of formation flight is also assessed with respect to attitude variations of the lifting bodies involved. The framework is also employed to determine the optimal position of blended-wing-body unmanned aerial vehicles in tandem formation flight.

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Section: Introductionmentioning

confidence: 97%

A Multi-Fidelity Approach for Aerodynamic Performance Computations of Formation Flight

et al. 2018

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“…In a formation flight, the airflow around the front plane receives strong disturbances, and forms a complicated wake field downstream of components such as the wing and fuselage, which is the main reason for affecting the aerodynamic characteristics of the rear plane. Through theoretical analysis [2,3], numerical calculations [4,5], wind tunnel tests [5,6], and flight tests [7,8], the aerodynamic characteristics of the rear aircraft at different relative positions in the formation flight can be obtained, thereby deriving the optimal position of the formation to maintain maximum aerodynamic gain. But there is another problem that should be concerned: how to arrive or leave the optimal position safely?…”

Section: Introductionmentioning

confidence: 99%

Numerical study on aerodynamic performance during the process of entering the formation flight

Wang,

Li,

et al. 2024

J. Phys.: Conf. Ser.

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. Two or more planes can fly in close formation similar to migratory birds, making use of the wing-tip vortex of the leader plane to increase lift and reduce drag, thereby effectively improving the flying range. By conducting wind tunnel tests and numerical simulations, the aerodynamic performance of formation flight at different relative positions can be obtained, the optimal formation position can thereby be solved. However, significant nonlinear and unsteady aerodynamic characteristics, induced by the interference between the follower plane and the wing-tip vortices of the leader plane, will affect the flight safety of the whole formation. At present, there is no effective prediction methods. Numerical simulations adopting adaptive grid refinement and dynamic overset grid were conducted for the dynamic entering process of the formation flight containing two Ty-154 planes. The aerodynamic characteristics and vortex interferences were analysed considering the effects of approaching direction and speed. The results indicate that there is deterioration of stability at the position where maximum lift gain is reached; Compared to the entering speed, the impact of directions on dynamic aerodynamic characteristics is more significant.

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“…The development of small, portable, mini or micro air vehicles, with limited maximum dimensions, has reignited interest in low-aspect-ratio (AR) aerodynamics [1][2][3][4][5]. Apart from common requirements such as maneuverability, take-off/landing performance and payload maximization, low AR wings should fly safely at reduced airspeeds, close to stall, in unsteady or gusty environments.…”

Section: Introductionmentioning

confidence: 99%