... =chordwise direction vector of parafoil n =normal direction vector of parafoil v _n=chordwise direction vector of flow velocity v _t=spanwise direction vector of flow velocity ρ=air density, kg/m³...

...Esmaeel Eslami; Mehran Tadjfar; Saman Najafi Purpose The purpose of this paper is to investigate the flow around Parastoo UAV's wing, with the aim of improving its aerodynamic performance. A major source of concern is the use of relatively large flaps in the original design. This unmanned aerial...

... in the simulations. The commercial CFD code ANSYS‐CFX was used to compute the flow field inside the flow domain of each case considered. The Reynolds averaged Navier‐Stokes (RANS) equations are discretized using an implicit, vertex‐based finite volume method, combined with the shear stress transport (SST) two...

...Nizam Dahalan; Shuhaimi Mansor; Muhammad Haniff Shaharudin; Airi Ali Purpose The purpose of this paper is to evaluate the synthetic jet actuator design's performance based on piezoelectric diaphragms that can be appropriately used for flow separation control. Design/methodology/approach Design...

... than a single injection system with the same mass flow rate. The study shows that when the distance between two ports is 8.5 times of the injection port's diameter (or more) and in the same time the first injection port is at least 1 throat diameter far from the nozzle throat, this system will show...

... is the reduction of emission current. This paper aims to discuss the minimum emission current of operating FEEP thrusters. Design/methodology/approach In this work, theoretical models, including fluid‐flow model and ion formation model, are analyzed. Current densities of these models are discussed...

...Hamed Sadeghi; Mahmoud Mani; S.M. Hossein Karimian Purpose The primary purpose of this paper is to investigate the characteristics of the unsteady flow field in the wake of Eppler‐361 airfoil undergoing harmonic pitch oscillation in both pre‐stall and post‐stall regimes. Design/methodology...

... M_x^m,M_y^m,M_z^m=blade root moments of mth blade measured in rotating frame p =modal displacement vector R=rotor radius (m) Helicopters Vibration measurement Aerodynamics Flow C...

...Erol Uzal; Sule Kapkin Purpose The purpose of this paper is to investigate the linear vibrations of an elastic plate subject to irrotational, incompressible fluid flow bounded by a rigid cylinder. Design/methodology/approach The plate is placed diametrically in the cylinder and extends along...

... performance. In this paper, possibility of changing the airfoil shape to improve its aerodynamic performance is studied. For this purpose, six different geometric shapes of the airfoil are investigated numerically to determine the best airfoil on the basis of lift and drag coefficients. Flow over the airfoil...

...S. Askari; M.H. Shojaeefard Purpose The purpose of this paper is to show how flow over the airfoil comprising a cross flow fan has been solved by developing a computational fluid dynamics (CFD) code. This research was going to find aerodynamic coefficients and static pressure distribution over...

... Helicopters Flow Flight dynamics © Emerald Group Publishing Limited 2009 σ=rotor solidity, stress components (…)^K=deformed blade reference frame=(1^K, 2^K, 3^{K) (…)L=local blade sectional reference frame=(1L}...

... for high‐speed turbo machinery components. Design/methodology/approach One of the most important issues in CFD is analysis of flow field in turbo machines. Flow in high‐speed radial turbo machinery is a 3D, turbulent and unsteady behavior so needs suitable method for converging. It is clear...

...A. Tuck; J. Soria Purpose The aims of this study were to investigate the effect of using a wall‐normal, 2D micro zero‐net‐mass‐flux (ZNMF) jet located at the leading edge of a NACA 0015 airfoil to actively control flow separation and enhance lift. Design/methodology/approach Experiments were...

... jets do not adversely influence the wall pressure distribution. Research limitations/implications As a result of developments in space flights and missile technology, the base flows at high Reynolds numbers continues to be an important area of research. Our understanding of many features of base...

... are solved for internal flow in the nozzle. Findings The results indicate that the nozzle design can be performed successfully and quickly by using the implemented algorithm. It is observed that using the method decreased CFD solver calls about 21 and 46 per cent for transonic and supersonic flow...

...Aytac Arikoglu; Ibrahim Ozkol Purpose To study the flow of a two‐dimensional, steady, incompressible and constant property fluid over a semi‐infinite flat plate represented by the well‐known Blasius equation. Design/methodology/approach Differential transform method was used to solve...

... is characterized by search and computational time to achieve satisfying solutions. In order to obtain more robust and faster algorithm, vibration concept, our earlier study, is further developed. This developed VGA is coupled with a full potential flow‐field solver for inverse design and airfoil optimisation...

...Ji‐Huan He By the semi‐inverse method proposed by He, a variational principle is established for steady flow over a thin, symmetric, non‐lifting aerofoil. The nonlinear, small‐disturbance, velocity‐potential equation is obtained by minimizing the obtained functional, and all boundary conditions...

...Jung‐Chul Shin The potential flow field for the transitional region in a constant radius, two‐dimensional duct was studied. The potential velocity and pressure profiles in various duct geometries with different turning angles and duct heights were investigated. A generalized solution of potential...