Numerous experiments have been conducted on plunging Eppler 361 airfoil in a subsonic wind tunnel. The experimental tests involved measuring the surface pressure distribution over the airfoil at Re=1.5×105. The airfoil was equipped with Gurney flap(heights of 2.6, 3.3 and 5% chord) and plunged at 6cm amplitude. The unsteady aerodynamic loads were calculated from the surface pressure measurement...

We present an experimental investigation of the flow structure in near wake a NACA0012 airfoil plunging sinusoidally at chord Reynolds number Re = 20 000 and for wide range reduced frequency k Strouhal based on peak-to-peak amplitude St . Estimated mean thrust coefficients using fluctuating velocity fields confirm 2 dependence as well significant effect ? 1. Generally, time-averaged quantities ...

Plunging airfoils are investigated for applications such as Micro-Air Vehicles (MAVs) and bird and fish like propulsion. Plunging or flapping wings can provide more propulsive efficiency than that of fixed wings, especially at small to moderate Reynolds numbers, where the MAVs (due to their small size) operate. Furthermore, it has been observed that birds and insects rely on detaching and separ...

Natural flight has consistently been the wellspring of many creative minds, yet recreating propulsive systems natural flyers is quite hard and challenging. Regarding design, biomimetics offers a wide variety solutions that can be applied at low Reynolds numbers, achieving high performance maneuverability systems. The main goal current work to computationally investigate thrust-power intricacies...

Abstract The peak loads experienced by aircraft of all scales will typically be during gusts, turbulence or extreme manoeuvres. Understanding the aerodynamic response to these transient disturbances is therefore crucial, particularly when Leading-Edge Vortices (LEVs) occur. This fundamental study investigates a wide range plunging motions. exhibited strong dependence motion amplitude yet remain...

A new fully-implicit approach for computing transonic aeroelastic solutions is presented. The unsteady Euler equations are coupled with a typical section swept wing model and integrated forward in time. The implicit Euler equations are integrated in pseudo-time using multigrid methods, and are coupled with a first-order system decomposition of the structural modal equations. Full convergence of...

High-fidelity numerical simulations with the spectral difference (SD) method are carried out to investigate the unsteady flow over a series of oscillating NACA 4-digit airfoils. Airfoil thickness and kinematics effects on the flapping airfoil propulsion are highlighted. It is confirmed that the aerodynamic performance of airfoils with different thickness can be very different under the same kin...