AD-P004 168 AD-P004 169 TITLE: Superroaneuverability. Wing Rock Flov Phenomena. Potential Applications of Forced Unsteady Flows. Unsteady Stall Penetration of an Oscillating Swept Wing. Simultaneous Flow Visualization and Unsteady Lift Measurement on an Oscillating Lifting Surface. A Visual Study of a Delta Wing in Steady and Unsteady Motion. Comparative Visualization of Accelerating Flow aroun...

Results of a high-speed 10-stage axial-flow compressor test involving overall compressor and individual stage performance while stalling and operating in quasi-steady rotating stall are described. Test procedures and data acquisition methods used to obtain the dynamic stalling and quasi-steady in-stall data are explained. Unstalled and in-stall time-averaged data obtained from the compressor op...

The unsteady separated turbulent flow around an oscillating airfoil pitching in a sinusoidal pattern in the regime of low Reynolds number is investigated numerically employing the URANS approach with two advanced turbulence models, namely the RNG kmode and Transition SST model, and the DES approach based on the SST kmodel. A comparison with experimental data shows that the SST kbased D...

This study employs a numerical simulation method that combines the plasma body force model based on electrostatics with Navier–Stokes equations to investigate coupling mechanism of flow fields induced by multistage dielectric-barrier discharge (MDBD) actuation. Compared conventional single-stage alternating-current DBD (AC-DBD) actuation, MDBD actuation provides higher intensity and larger cont...

1. Abstract A computational approach is described for the rapid and systematic prediction and evaluation of the onset of dynamic stall due to rapid incidence changes or unsteady pitch or plunge motions. The method combines an unsteady, two-dimensional panel code with a two-dimensional boundary-layer code. The panel code provides incompressible, inviscid owwelds about arbitrary airfoils undergoi...

A comparative study of two combined blowing/suction flow control methods was conducted on the pitching airfoil using unsteady Reynolds-averaged Navier–Stokes (URANS) method. One used leading-edge blowing and trailing-edge suction, which is referred to as a co-flow jet (CFJ), conformal slot CFJ (C-CFJ) adopted. Another suction with blowing, called reversed (R-CFJ). The S809 baseline its stall ch...

Abstract. Accurate modeling of the dynamic stall remains a challenge for design and construction turbine blades helicopter rotors. At same time, wind turbines, instance, are becoming steadily larger, further increasing demands on their structure necessitating even more detailed forces at hand. The primarily used (semi-)empirical models today have long research history invariably based phase-ave...

Abstract Dynamic stall, which has a significant effect on the aerodynamic performances of dynamic airfoils, is closely related to physics stall vortex (DSV). The DSV NACA 0012 airfoil was experimentally studied using unsteady pressure measurements with high time accuracy. experimental Reynolds number Re = 1.5 × 10 6 , and reduced frequency k 0.069. propagation field during process analyzed in d...