Body-fin interference on the Magnus effect of spinning projectile in supersonic flows

Yin, Jintao; Wu, Xiaojiang; Lei, Juanmian

doi:10.1080/19942060.2017.1319878

Cited by 10 publications

(11 citation statements)

References 27 publications

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“…More results at Ma = 2.5 under different angles of attack can be found in the authors' previous study. 4 In subsonic conditions, the absolute value of the computed results is smaller than that of experimental data, and the results from different turbulence models are similar. The previous study showed that the situation can be improved using the hybrid Reynolds-averaged Navier-Stokes/large eddy simulation (RANS/LES) method, while this was for the configuration with boat tail and the errors were still unneglectable.…”

Section: Validation Of Numerical Methodsmentioning

confidence: 82%

Canards interference on the Magnus effect of a fin-stabilized spinning missile

Yin

Lei

et al. 2018

Advances in Mechanical Engineering

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Reynolds-averaged simulations of flow over spinning finned missiles with and without canards were carried out at Ma = 0.6, 0.9, 1.5, and 2.5; a= 4°, 8°, and 12.6°; and v = 0:025 to investigate different mechanisms of the Magnus effect. An implicit dual-time stepping method and the g À Re ut transition model were combined to solve the unsteady Reynolds-averaged Navier-Stokes equations. Grid independence study was conducted, and the computed results were compared with archival experimental data. The transient and time-averaged lateral force coefficients were obtained, and the flow field structures were compared at typical rolling angles. The results indicate that in subsonic conditions, the canards interference intensifies the asymmetrical distortion of the body surface boundary layer and flow separation at different angles of attack, doubling the absolute value of the time-averaged body lateral force; the wash flow effect strengthens on the leeward tail due to the canards interference, increasing its time-averaged lateral force; in supersonic conditions, the shock and expansion waves induced by canards, the vortex system, and the flow separation are responsible for the fluctuation of the body lateral force; the direction of the canard induced wash flow alters as angle of attack increases, increasing first and then decreasing the time-averaged tail lateral force.

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Section: Validation Of Numerical Methodsmentioning

confidence: 82%

Canards interference on the Magnus effect of a fin-stabilized spinning missile

Yin

Lei

et al. 2018

Advances in Mechanical Engineering

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“…The aerodynamic characteristics of tailed rotating missiles have been also investigated through numerical simulations. Yin et al [13] carried out numerical calculations on a finner, compared the calculated results with the experimental values of AEDC [14], and found that the calculated values of the transition SST model were close to the experimental values. Therefore, the transition SST model was adopted in the present work.…”

Section: Introductionmentioning

confidence: 81%

“…It was found that the SST k-ω model performed well in an adverse pressure gradient and separation flow. However, the SST k-ω model causes the phenomenon of overprediction in the calculation of the rotating missile Magnus force [13]. The transition SST model works based on the SST k-ω model and considers the following two parameters-intermittent factor and local boundary layer momentum thickness-to construct two transport equations.…”

Section: Turbulence Modelmentioning

confidence: 99%

“…Combining these two transport equations and relevant empirical formulas with the SST k-ω turbulence model, the four-equation transition SST model can be established. The turbulence model is more sensitive to factors affecting transition, such as turbulence intensity, separation, and pressure gradient, and is more accurate than other turbulence models in the calculation of the rotational missile Magnus force [13].…”

Section: Turbulence Modelmentioning

confidence: 99%

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Analysis of the Magnus Moment Aerodynamic Characteristics of Rotating Missiles at High Altitudes

Chen

Zhou

2021

International Journal of Aerospace Engineering

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The Magnus moment characteristics of rotating missiles with Mach numbers of 1.3 and 1.5 at different altitudes and angles of attack were numerically simulated based on the transition SST model. It was found that the Magnus moment direction of the missiles changed with the increase of the angle of attack. At a low altitude, with the increase of the angle of attack, the Magnus moment direction changed from positive to negative; however, at high altitudes, with the increase of the angle of attack, the Magnus moment direction changed from positive to negative and then again to positive. The Magnus force direction did not change with the change of the altitude and the angle of attack at low angles of attack; however, it changed with altitude at an angle of attack of 30°. When the angle of attack was 20°, the interference of the tail fin to the lateral force of the missile body was different from that for other angles of attack, leading to an increase of the lateral force of the rear part of the missile body. With the increasing altitude, the position of the boundary layer with a larger thickness of the missile body moved forward, making the lateral force distribution of the missile body even. Consequently, Magnus moments generated by different boundary layer thicknesses at the front and rear of the missile body decreased and the Magnus moment generated by the tail fin became larger. As lateral force directions of the missile body and the tail were opposite, the Magnus moment direction changed noticeably. Under a high angle of attack, the Magnus moment direction of the missile body changed with the increasing altitude. The absolute value of the pitch moment coefficient of the missile body decreased with the increasing altitude.

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“…The afterbody of the missile is decoupled from the forebody by a bearing, thus avoiding the transmission of the reverse rolling moment of the tail section to the forebody, which can effectively solve the reverse rolling problem. However, because of the Magnus effect of the spinning afterbody, the missile has yaw motion (Morote, 2005;Yin et al, 2017). Moreover, the free-spinning tail missile has obvious nonlinear aerodynamic characteristics, which have a high requirement on the missile control system (Lesieutre et al, 2002).…”

Section: Introductionmentioning

confidence: 99%

The numerical investigation on the rolling decoupling of a canard-controlled missile using the jet control system

Zhang

Lei

Yin³

et al. 2020

Engineering Applications of Computational Fluid Mechanics

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When the canard-controlled missile is conducting roll control, the asymmetric downwash induced by the canard impacts on the fins and produces a reverse rolling moment, resulting in the aerodynamic coupling between the canards and the fins. The rolling coupling can cause the reduction and even failure of the missile roll control. However, the current rolling decoupling methods always have adverse effects on the lift-drag ratio or flight stability of the missile. Based on the numerical simulation, this paper proposes a new method to reduce the roll coupling by adding a jet system between the canards and the fins. The effect of jet control was obtained under different freestream conditions. The influence of jet control factors on the missile aerodynamic characteristics was investigated and analyzed. The outcomes demonstrate that the jet control can effectively decrease the roll coupling between the canards and the fins, and eliminate the reverse rolling problem in most cases. With the same mass flow rate, the control effect is better at lower Mach number. Jet location and jet mode have a higher influence on the control effect. An optimal mass flow rate exists for the best control efficiency. This decoupling method is simple in structure and can reduce the side force and yawing moment without destroying the lift-drag ratio.

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Body-fin interference on the Magnus effect of spinning projectile in supersonic flows

Cited by 10 publications

References 27 publications

Canards interference on the Magnus effect of a fin-stabilized spinning missile

Canards interference on the Magnus effect of a fin-stabilized spinning missile

Analysis of the Magnus Moment Aerodynamic Characteristics of Rotating Missiles at High Altitudes

The numerical investigation on the rolling decoupling of a canard-controlled missile using the jet control system

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