On the lift curve slope for rectangular flat plate wings at moderate Reynolds number

Gutiérrez-Castillo, Paloma; Aguilar-Cabello, Jorge; Alcalde-Morales, Sergio; Parras, Luis; Pino, C. del

doi:10.1016/j.jweia.2020.104459

Cited by 7 publications

(9 citation statements)

References 30 publications

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“…Theoretical lift curve slope, C Lα for FWMAV was also calculated using Kuchemann equation as discussed by Anderson 50 and Gutierrez-Castillo in Ref. 51. The theoretical lift curve slope in the linear region came out to be 4.1107/rad.…”

Section: Numerical Simulations Of Fwmav For the Calculation Of Pitch ...mentioning

confidence: 92%

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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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Section: Numerical Simulations Of Fwmav For the Calculation Of Pitch ...mentioning

confidence: 92%

“…Theoretical lift curve slope, C Lα for FWMAV was also calculated using Kuchemann equation as discussed by Anderson 50 and Gutierrez-Castillo in Ref. 51. The…”

Section: Validation Of Static Steady Simulationmentioning

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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show abstract

“…Wing model forces were obtained under different conditions using a wind tunnel located at the aero-hydrodynamic lab at the University of Málaga. The wind tunnel has a 1×1 m 2 cross-section with low turbulence (of the order of 0.8%, see more details in [20]). Each wing model has a c = 100 mm chord, with a length, l, from 100 to 400 mm, avoiding relevant (solid and wake) blockage effects.…”

Section: Outline Of the Experimentsmentioning

confidence: 99%

“…Due to the importance of C Lα , correlations have been proposed in the literature to approximate this parameter for various ranges of Re and AR. Since NACA0012 wing models are relatively thin symmetric profiles, we could try to estimate a first approximation of C Lα value using the correlation provided by Gutiérrez-Castillo et al [20] for a flat plate (which was obtained for the same range of α that our study):…”

Section: Clα Correlationmentioning

confidence: 99%

“…This latter parameter has been studied in the literature for different wing shapes due to its connection to flight requirements and their influence on induced drag computation [17][18][19]. A recent study has provided correlations of the C Lα of a straight flat plate for any aspect ratio (between 1 and 8) and Reynolds number (ranging from 40 to 200×10 3 ) [20]. However, the estimations of C Lα for NACA0012 wing models become more complicated due to the appearance of non-linear effects as the production of negative lift at positive and small angles of attack near zero at moderate Reynolds number [21].…”

Section: Introductionmentioning

confidence: 99%

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Influence of passive deformation in the lift coefficient of a NACA0012 wing model

Duran,

Lorite-Díez,

Konovalov-Shishov

et al. 2024

European Journal of Mechanics - B/Fluids

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Sectional analysis of revolving wings: Effect of leading-edge and trailing-edge vortices

Namdeo¹,

Samir²,

Deepu³

2021

European Journal of Mechanics - B/Fluids

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On the lift curve slope for rectangular flat plate wings at moderate Reynolds number

Cited by 7 publications

References 30 publications

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

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

Influence of passive deformation in the lift coefficient of a NACA0012 wing model

Sectional analysis of revolving wings: Effect of leading-edge and trailing-edge vortices

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