CFD based determination of dynamic stability derivatives in yaw for a bird

Moelyadi, Mochammad Agoes; Sachs, Gottfried

doi:10.1016/s1672-6529(07)60033-x

Cited by 11 publications

(8 citation statements)

References 7 publications

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“…Jones and Platzer [1] made their contribution by calculating the in viscid flow for two-dimensional airfoils in plunging and pitching motion in comparison with analytical results. Moelyadi and Sach [2] have simulated flapping motion with a small dihedral angle for calculating dynamic stability derivatives in the yaw for a bird. Also, aerodynamic effects on birds with a large dihedral angle have been studied [3].…”

Section: Unsteady Aerodynamics Of Flapping Wing Of a Birdmentioning

confidence: 99%

Unsteady Aerodynamics of Flapping Wing of a Bird

2013

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The unsteady flow behavior and time characteristics of the flapping motion of a bird computational method. During wing surfaces and surrounding flow flow changes in the flow of flapping speed on unsteady aerodynamic load, two kinds of computational simulations were carried out, namely To mimic the movement of flapping path accorded dihedral angle and time. The computations of time based on the solution of applying the k-ε turbulen computational domain around the model use provide more accuracy wing and body surfaces research, the seagull bird pointed wing-tips and movement, velocity contours as well as aerodynamic coefficients of motion of the bird at various flapping

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Section: Unsteady Aerodynamics Of Flapping Wing Of a Birdmentioning

confidence: 99%

Unsteady Aerodynamics of Flapping Wing of a Bird

2013

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“…Moreover, the Reynolds number of the wind-tunnel experiment is smaller than the practical flight Reynolds number. With the development of computational fluid dynamics (CFD) and computers, CFD can be used as an important approach for the computation of the dynamic derivatives of different objects [3][4][5][6][7][8][9][10][11]. Dynamic yaw stability derivatives of a gull bird have been determined using the CFD method [3].…”

Section: Introductionmentioning

confidence: 99%

“…With the development of computational fluid dynamics (CFD) and computers, CFD can be used as an important approach for the computation of the dynamic derivatives of different objects [3][4][5][6][7][8][9][10][11]. Dynamic yaw stability derivatives of a gull bird have been determined using the CFD method [3]. Calculations on dynamic derivatives for various aerodynamic aircraft and submergible vehicles using CFD have been investigated in previous research [4][5][6][7][8][9][10][11].…”

Section: Introductionmentioning

confidence: 99%

Computational Fluid Dynamics Predictions of Stability Derivatives for Airship

Wang

2012

Journal of Aircraft

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In this paper, an approach that can obtain the stability derivatives through the unsteady computational fluid dynamics approach and Fourier analysis is proposed. Hybrid grids composed of boundary-layer viscous structure meshes and unstructured meshes were used. The flowfield was divided into two regions: the inner region and the outer region. The dynamic deformation grid was updated through the grid move with the body in the inner region and spring analogy in the outer region. This method can keep the quality of mesh preferably than one whole region dynamic mesh method during the course of movement of body. The validity of the computational method and dynamic mesh approach was verified by the calculation of the AGARD NACA 0012 airfoil. The calculation method of stability derivatives was verified by 6:1 prolate spheroid. The effects of the presence of the fins on stability derivatives of the airship were analyzed in this paper. The method proposed in this paper can be used to calculate the stability derivatives for other aircraft and submarine vehicles. Nomenclature a = the amplitude of oscillation c = the airfoil chord length F z = the normal force F w z = the stability derivatives of longitudinal force about velocity, F w z @F z =@w F _ w z = the stability derivatives of longitudinal force about velocity acceleration, F _ w z @F z =@ _ w F s x;y;z = the nondimension stability derivatives of force, F s x;y;z F s x;y;z V 1 S ref L ref =4 ft = the function of time k = the reduced frequency L ref = the reference length M y = the pitching moment M y = the stability derivatives of pitching moment about angle of attack, M y @M y =@ M _ y = the stability derivatives of pitch moment about acceleration angle of attack, M _ y @M y =@ _ M q y = the stability derivatives of pitch moment about pitch angle velocity, M q y @M y =@q M _ q z = the stability derivatives of pitch moment about pitch angle acceleration velocity, M _ q y @M y =@ _ q M s x;y;z = the nondimension stability derivatives of moment, M s x;y;z M s x;y;z V 1 S ref L 2 ref =4 q = the pitch angle velocity, q _ # S ref = the reference area T 0 = the period of one cycle of unsteadiness, T 0 2=$ t = the time V 1 = the freestream velocity # = the pitch angle w = the longitudinal oscillation velocity _ w = the longitudinal oscillation acceleration $ = the frequency of oscillation x = the nondimension state variable,x x 2V 1 =L ref z = the longitudinal oscillation displacement m = the mean angle of pitching 0 = the amplitude of pitching = the angle of attack, # _ = the accelerate of angle of attack, _ _ # t = the time step, t T 0 =400 ii = the added mass, ii , (i 1; 2; . . . 6)

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“…For instance, Moelyadi worked on a UAV and used an amplitude of ± 0.5° for dynamical analysis. 37 Wu Z researched on DLR and he oscillated the aircraft within ± 2.5° 30 ± 1° amplitude was used by Baigang for finner missile, 27 Chen utilized ± 5° for NACA 0012 airfoil 38 and Liu X. worked on rockets dynamics and used an amplitude of ± 1° to study rocket dynamics. 39 A summary is shown in Table 1.…”

Section: Time-domain Methods To Compute Cmq and Cmtrueα˙mentioning

confidence: 99%

Numerical estimation of longitudinal damping derivatives of a flying wing micro aerial vehicle

Shams

Shah

Shahzad

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Longitudinal damping derivatives, [Formula: see text], of an aerial vehicle is important from an aerodynamic stability point of view. Experimental calculation of longitudinal damping derivatives using wind tunnel is not a cost-effective method; therefore, researchers have developed numerical solutions as an alternative. In this research, the longitudinal damping derivatives of a flying wing micro aerial vehicle (FWMAV) were calculated using numerical simulations by adopting pull-up maneuver and forced harmonic motion in pitch axis. Pull-up maneuver with four steady rotational rates was simulated to obtain pitch rate derivative, C mq. Combined derivative, [Formula: see text], was obtained by simulating forced harmonic motion of FWMAV around a mean angle of attack of 0° with amplitude of oscillation of ± 3° using four reduced frequencies (0.02, 0.03, 0.04, and 0.05). Unstructured surface and volume mesh was used in a spherical domain engulfed inside a large cuboid domain for moving reference frame strategy. Reynolds number taking mean aerodynamic chord as a reference length was 2.33 × 105. Spalart–Allmaras turbulence model was used. Pitch rate derivative, combined derivative, and acceleration derivative were found as − 0.03/rad, − 7.39/rad, and − 7.36/rad, respectively, by the use of a phase method at a reduced frequency of 0.03. During flight dynamic analysis, it was found that [Formula: see text] has a significant contribution on damping in short period mode with no effect on Phugoid mode. The research concluded that for tailless configurations, acceleration derivative [Formula: see text] can exist and can provide necessary damping in the longitudinal flight mode.

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CFD based determination of dynamic stability derivatives in yaw for a bird

Cited by 11 publications

References 7 publications

Unsteady Aerodynamics of Flapping Wing of a Bird

Unsteady Aerodynamics of Flapping Wing of a Bird

Computational Fluid Dynamics Predictions of Stability Derivatives for Airship

Numerical estimation of longitudinal damping derivatives of a flying wing micro aerial vehicle

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