[PDF] Top 20 Computational Study of Aspect-Ratio Effects on Swept-Wing Stall.

... the effects of aspect ratio on the behavior of boundary-layer separation along the span on swept wings, as well as extend the development of an aerodynamic database of airfoils and wings ... See full document

... the effects of a separated boundary layer have seen some ...the effects of the separated boundary layer with a reduction in camber of the lifting surface of a potential-flow method such as the vortex ... See full document

... The study investigated several aerofoil section profiles, wing planforms and wing optimisation to achieve the desired performance characteristics using the Xfoil and the VSaero computational ... See full document

... and wing area varies through the loss of feathers (and consequently wing area) as a result of moult and feather ...in wing morphology in relation to body mass. Wing loading increases by 60% in ... See full document

... Another avenue for research is to apply the method to cases with angular velocities — roll, pitch, and yaw. The presence of angular velocities changes the operating α of the sections, and this change is not necessarily ... See full document

... The author would like to express gratitude to Kyla Alcia Tambunan, Fauni Ambarsari, Andhika S. Pratama, Ilham Fahmi Allam, Haidar Azhar Yazid, Dwi Novarifanto, and Sofiana Ulfah for their work and collaboration during ... See full document

... The “shear force”, haemodynamic force acting parallel to the stent, may lead to stent migration with serious con- sequence. During the systole phase, the shear force per unit area on the stent amounts to 10.49 N·m –2 (AR ... See full document

... the wing sections over the limited angle-of-attack range do indicate some of the same behaviors that were observed earlier in the streamline plots and spanwise lift distributions in the work of Petrilli ... See full document

... down towards its initial orientation (Fig.1). These actions were recorded via high-speed videography and used to: (1) identify the wing kinematics used to perform the manoeuvre and (2) measure the closed-loop ... See full document

... surface wing flaps, known as spoiler, are typically used to reduce lift and increase drag at touchdown; however spoilers have been shown to in- crease lift and reduce drag at near-stall ... See full document

... the ratio of body mass to wing area—known as “wing loading”—has a strong influence on the amount of thrust generated per wingbeat (Dudley, ...this study I am most interested in the third ... See full document

... (Tobalske et al., 2009). These values are not directly comparable with those of the gliding swift, because the zebra finches exhibit a body angle of attack to generate lift, which causes increased parasite drag. A ... See full document

... with swept wings to attain higher critical Mach speeds which is very less in straight wing trainer ...Aircraft’s. Swept wings are preferred for its high lift to drag ratio low speed takeoff ... See full document

... For low inertia, wing span should be small but wing-tip length index T\ should be large long hand wings, wing-tip shape index /should be small pointed tips and aspect ratio AR should be [r] ... See full document

... The alcids have met these conflicting selection pressures by using partially folded wings while diving (Stettenheim, 1959; Spring, 1971). Furthermore, alcids have relatively small wings which, it has been suggested, are ... See full document

... the wing surface owing to the method we used for fi ltering out re fl ections from the wing surface ( section ...present study corresponds to ...the wing surface were used to visualize ... See full document

... the wing is not a real 2D. Airfoil varies along its span. Typically, the wing has a ...the wing the angle of attack is greater than the angle of attack at the wing ...past wing segment ... See full document

... calculated wing area from the two wings and added 10 % for body area (according to Norberg and Rayner, 1987) when measurements of body area were ...and wing measurements are, however, quite different from ... See full document

... the swept wing analogy and tip vortex hypothesis? We found that LEV stability induced by the tip vortex does not seem to work for fly wings at Re = 110 and 1400 (Figs 1 and 2), although there is evidence ... See full document

... behavior, ascent velocity is positively correlated with flapping frequency even within the small range of 1–2·Hz (R.D., B.J.B. and J.A.G., unpublished data). In pteropods, stroke amplitude is near maximal during ascent ... See full document