Results 231 to 240 of about 8,670 (264)
Some of the next articles are maybe not open access.
21st Aerospace Sciences Meeting, 1983
At freestream Mach numbers above M= 0 3 shock/boundary layer interaction begins to complicate the unsteady airfoil stall characteristics The present paper shows how theoretical relationships can be developed for the interdependence between unsteady and steady characteristics to provide the means whereby the shock induced dynamic stall characteristics ...
L. E. Ericsson, J. P. Reding
openaire +1 more source
At freestream Mach numbers above M= 0 3 shock/boundary layer interaction begins to complicate the unsteady airfoil stall characteristics The present paper shows how theoretical relationships can be developed for the interdependence between unsteady and steady characteristics to provide the means whereby the shock induced dynamic stall characteristics ...
L. E. Ericsson, J. P. Reding
openaire +1 more source
A Phenomenological Model of Dynamic Stall
SAE Technical Paper Series, 2002<div class="htmlview paragraph">Dynamic stall has been the subject of much research but there is still some uncertainty about several aspects. Almost all research to date has involved experiments or computational fluid dynamics, both, in essence, trying to duplicate the phenomena. The present research takes a different tack by trying to develop a
openaire +1 more source
Toward dynamic separation without dynamic stall
Experiments in Fluids, 1988The concept of vorticity separation without dynamic stall is illustrated by flow visualization. A small airfoil with a rotating nose, originally built for the demonstration of static stall control, was placed in a wind tunnel and dynamically pitched. The flow around the airfoil during pitch was successfully visualized and filmed.
P. Freymuth, S. Jackson, W. Bank
openaire +1 more source
Analysis of Dynamic Stall using Dynamic Mode Decomposition Technique
31st AIAA Applied Aerodynamics Conference, 2013Dynamic mode decomposition is applied to investigate the unsteady flowfield around a pitching airfoil. The extracted flow structures are termed as dynamic mode decomposition modes. Analyses are performed for both attached flow and dynamic stall cases. Initially, flowfield data generated from numerical simulations are investigated.
Mariappan, Sathesh +3 more
openaire +2 more sources
Control of Compressible Dynamics Stall Using Microjets
Volume 2: Symposia, Parts A, B, and C, 2003Control of the dynamic stall process of an NACA 0015 airfoil undergoing periodic pitching motion is investigated experimentally in a high-speed wind tunnel facility. Multiple microjet nozzles distributed uniformly in the first 15% chord from the airfoil’s leading edge are used for the control. Point Diffraction Interferometry (PDI) technique is used to
Shih, C. +3 more
openaire +2 more sources
A computational study on the dynamic stall of a flapping airfoil
16th AIAA Applied Aerodynamics Conference, 1998The dynamic stall boundaries of a NACA 0012 airfoil oscillating in either the pure plunge mode or in the combined pitch and plunge mode is computed using a thin-layer Navier-Stokes solver. Unsteady flowfields are computed at the free-stream Mach number of 0.3, the Reynolds number of 1 • 10, and the Baldwin-Lomax turbulence model is employed.
Tuncer, Ismail +2 more
openaire +2 more sources
Design and development of a compressible dynamic stall facility
Journal of Aircraft, 1989A dynamic stall facility offering a unique new capability for studies of compressibility effects on dynamic stall is described. This facility features complete visual access by mounting the test airfoil between optical-quality glass windows which are rotated in unison to produce the oscillating airfoil motion associated with helicopter rotor dynamic ...
Chandrasekhara, M., Carr, L.
openaire +3 more sources
Compressible studies on dynamic stall
27th Aerospace Sciences Meeting, 1989The purpose of this work is to investigate the effects of compressibility on the dynamic stall phenomenon by numerical simulation of the unsteady flow. The full two-dimensional unsteady compressible Navier-Stokes equations are solved for flows over oscillating airfoils and airfoils pitching rapidly to high angles of attack.
openaire +1 more source
Review of rotating wing dynamic stall: Experiments and flow control
Progress in Aerospace Sciences, 2023Marilyn Smith +2 more
exaly