This paper deals with the optimization of a synthetic jet actuator parameters in the control flow around the NACA0015 airfoil at two angles of attack: 13° (i.e. the stall angle of NACA0015) and 16° (i.e. the post stall angle of NACA0015) to maximize the aerodynamic performance of the airfoil. Synthetic jet actuator is a zero mass flux-active flow control device that alternately injects and remo...

The velocity correction method for two-dimensional wind-tunnel testing is expanded for the case of testing airfoils between splitter plates. Despite the common nse of splitter plates, the peculiar effects of this testing arrangement on the velocity correction are not well documented. The use of splitter plates in the test section has several advantages, but there are unfortunate consequences (s...

Basing on the principle of virtual equivalent velocity, this paper adapt the method of extending axis flow impeller to the quasi 3-D flow design of diagonal flow impeller with the experimental cascade data of circular arc blade. The performances of diagonal flow fan with outlet guide volute designed by this method, are compared with that designed by airfoil section cascade data. The reasonablen...

Two deterministic incompressible flow solvers are coupled with a non-intrusive stochastic collocation method to propagate several aerodynamic uncertainties encountered in a standard trailing-edge noise experiment of a low-speed Controlled-Diffusion (CD) airfoil to predict the far-field noise. Reynolds-Averaged Navier-Stokes (RANS) and Large-Eddy Simulations (LES) are applied to the same restric...

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...

In this paper we carry out computational studies of three-dimensional flow over flapping wings. The problems we have investigated include, firstly, three-dimensonal simulation of flow over an extruded SD7003 airfoil in plunging motion at transitional Reynolds number and, secondly, flow over a pair of flapping rectangle wings with constant NACA0012 cross-sectional airfoil profile at low Reynolds...

1. Abstract A desirable feature in multidisciplinary design optimization is to achieve an acceptable preliminary or initial design in an expeditiously fashion. One way to pursue this goal is to decrease the number of design variables assigned to structural definition. To accomplish this reduction the optimization problem is formulated following the Spectral Level Set Methodology. According to t...

In the present study, a large number of acoustic simulations are carried out for a low noise airfoil with different Trailing Edge Serrations (TES). The Ffowcs Williams-Hawkings (FWH) acoustic analogy is used for noise prediction at trailing edge. The acoustic solver is running on the platform of our in-house incompressible flow solver EllipSys3D. The flow solution is first obtained from the Lar...

We present computations of membrane airfoil behavior subject to aerodynamic loading and compare them with in vivo measurements of membrane wings of bats during flight. The computational method assumes an inviscid potential flow (with net circulation determined by a Kutta condition), is computed using XFOIL and iteratively coupled with a finite element model describing the membrane behavior. We ...

Leading edge noise is a significant broadband noise source in aircraft engines, and is the primary broadband noise mechanism in outlet guide vane noise in turbofans, and broadband rotor wake interaction noise in contra-rotating open rotor engines. Previous authors have studied the effects of various aspects relating to this noise source, including airfoil geometry effects, cascade effects, and ...