Author: Iraj M. KalkhoranPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
An Experimental Investigation of the Parallel Vortex-airfoil Interaction at Transonic Speeds
Author: Iraj M. KalkhoranAn Experimental Investigation of the Perpendicular Vortex-airfoil Interaction at Transonic Speeds
Author: Iraj M. KalkhoranPublisher:
ISBN:
Category : Helicopters
Languages : en
Pages : 314
Book Description
Experimental Investigation of the Perpendicular Vortex-airfoil Interaction at Transonic Speeds
Author: Iraj Masbooghi KalkhoranPublisher:
ISBN:
Category :
Languages : en
Pages : 157
Book Description
An Experimental Investigation of the Parallel Blade-vortex Interaction
Author: An Experimental Investigation of Parallel Blade/vortex Interaction for a NACA0015 Airfoil
Author: Anastasios KokkalisPublisher:
ISBN:
Category : Aerofoils
Languages : en
Pages :
Book Description
Experimental Investigation of Three-Dimensional Vortex-Airfoil Interaction in A Supersonic Stream
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 82
Book Description
An experimental study of the interaction between stream-wise vortices and a two-dimensional surface was conducted in a Mach 2.5 flow. The influence of oblique shock wave intensity on the inherently three-dimensional interaction was examined for vortices of variable strength. Planar laser sheet visualizations of the flowfield generated by the interaction at several distances downstream of the wedge leading edge were performed in order to gain an understanding of vortex behavior at distances further downstream. Results indicated that the interaction of a moderate strength vortex with an oblique shock wave leads to the formation of a steady separated shock structure upstream of the oblique shock front. Planar laser sheet visualization of the flowfield revealed an expansion of the vortex core in crossing a strong oblique shock front. The vortical structure was observed to persist along the entire chord of the shock generating wedge but was seen to diffuse with distances downstream of the wedge leading edge. Measurements of the vortex center above the wedge surface indicated that immediately downstream of the normal portion of the bulged-forward shock wave the vortex center was parallel to the direction of the free stream flow. (AN).
An Experimental Investigation of the Parallel Blade-Vortex Interaction
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781725627840
Category :
Languages : en
Pages : 32
Book Description
A scheme for investigating the parallel blade vortex interaction (BVI) has been designed and tested. The scheme involves setting a vortex generator upstream of a nonlifting rotor so that the vortex interacts with the blade at the forward azimuth. The method has revealed two propagation mechanisms: a type C shock propagation from the leading edge induced by the vortex at high tip speeds, and a rapid but continuous pressure pulse associated with the proximity of the vortex to the leading edge. The latter is thought to be the more important source. The effects of Mach number and vortex proximity are discussed. Caradonna, F. X. and Laub, G. H. and Tung, C. Ames Research Center NASA-TM-86005, A-9850, NAS 1.15:86005, USAAVSCOM-TM-84-A-9 RTOP 992-21-01...
Research in Progress
Author: Scientific and Technical Aerospace Reports
Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 602
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author: George G. Mateer