This paper puts forward an aerodynamic design method to improve the high-speed performance of aircraft with low-aspect-ratio tailless configuration. The can ameliorate longitudinal moment characteristics configuration by designing and collocating key section airfoils constrains fixed parameters planform shape capacity. Firstly, effect twisting wing, fore-loading aft-reflexing on is evaluated hi...

A wing-design study has been conducted on a 65 swept leading-edge delta wing in which the wing geometry was modi ed to take advantage of the naturally occurring ow that forms over a slender wing in a supersonic ow eld. Three-dimensional nonlinear analysis methods were used in the study which was divided into three parts|preliminary design, initial design, and nal design. In the preliminary desi...

The aim of this paper is to provide an aeroelastic computational tool which determines the induced wing loads during flapping flight. For this purpose, a Finite Element (FE) code based on a four-node plate bending element formulation is developed to simulate the aeroelastic behavior of flapping wings in low incompressible flow. A quasi-steady aerodynamic model is incorporated into the aeroelast...

the carob moth, ectomyelois ceratoniae (zeller), belongs to the family pyralidae and the subfamily phycitinae. in spite of some features of sexual dimorphism in size and shape in the order lepidoptera and the mentioned family, it has not been recorded in this species. in the current study, sexual dimorphism in the wing shape and size of carob moth on four hosts (pomegranate, fig, pistachio and ...

Mesh Deformation is an important element of any fluid-structure interaction simulation. In this article, a new methodology is presented for the deformation of volume meshes using incremental radial basis function (RBF) based interpolation. A greedy algorithm is used to select a small subset of the surface nodes iteratively. Two incremental approaches are used to solve the RBF system of equation...

Extensive wind tunnel tests are conducted to evaluate surface pressure distribution of a semi span swept wing. The wing section has a laminar flow airfoil similar to NACA 6-series airfoils. The investigations are conducted at various speeds and angles of attack. Surface pressure distribution over the wing upper surface is measured for both chordwise and spanwise sections. Statistical analyses a...

The framework used to prove the multiplicative law deformation of the algebra of Feynman-Bender diagrams is a twisted shifted dual law (in fact, twice). We give here a clear interpretation of its two parameters. The crossing parameter is a deformation of the tensor structure whereas the superposition parameters is a perturbation of the shuffle coproduct of Hoffman type which, in turn, can be in...