An Experimental Investigation of the Parallel Blade-Vortex Interaction PDF Download
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781725627840
Category :
Languages : en
Pages : 32
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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...
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781725627840
Category :
Languages : en
Pages : 32
Get Book Here
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...
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 40
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Book Description
Author: Anastasios Kokkalis
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages :
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Author: Ali R. Ahmadi
Publisher:
ISBN:
Category : Vortex generators
Languages : en
Pages :
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Author: Henry E. Jones
Publisher:
ISBN:
Category : Unsteady flow (Aerodynamics)
Languages : en
Pages : 96
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Book Description
A study of the full-potential modeling of a blade-vortex interaction was made. A primary goal of this study was to investigate the effectiveness of the various methods of modeling the vortex. The model problem restricts the interaction to that of an infinite wing with an infinite line vortex moving parallel to its leading edge. This problem provides a convenient testing ground for the various methods of modeling the vortex while retaining the essential physics of the full three-dimensional interaction. A full-potential algorithm specifically tailored to solve the blade-vortex interaction (BVI) was developed to solve this problem. The basic algorithm was modified to include the effect of a vortex passing near the airfoil. Four different methods of modeling the vortex were used: (1) the angle-of-attack methods, (2) the lifting-surface method, (3) the branch-cut method, and (4) the split-potential method. A side-by-side comparison of the four models was conducted. these comparisons included comparing generated velocity fields, a subcritical interaction, and a critical interaction. The subcritical and critical interactions are compared with experimentally generate results. The split-potential model was used to make a survey of some of the more critical parameters which affect the BVI.
Author: Donald R. Wilson
Publisher:
ISBN:
Category :
Languages : en
Pages : 50
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Results from an experimental investigation of helicopter rotor blade-vortex interaction (BVI) phenomena at transonic Mach numbers and at Reynolds numbers representative of actual helicopter flight operations are presented. The study examined both perpendicular (vortex core perpendicular to the blade leading edge) and parallel (vortex core parallel to blade leading edge) interaction geometries. The significant results are: 1. Perpendicular Interaction: The effect of the vortex causes a large reduction in upper surface pressure distribution (lift increase). This lift increase correlates with strength of the vortex and closeness of the vortex encounter. The interaction is most pronounced near the leading edge of the airfoil. A large spanwise deflection of the vortex is observed as it passes over the airfoil. 2. Parallel Interaction: A similar reduction in upper surface pressure distribution is also observed during the transient passage of the parallel vortex over the airfoil. Like the perpendicular interaction, this effect is also most pronounced near the leading edge, which is in contrast to the general results of numerous CFD simulations. For certain combinations of vortex strength and encounter distance, a class-C shock motion (forward propagation of the airfoil shock wave) was observed. Keywords: Blade vortex interaction; Transonic aerodynamics. (jhd).
Author: Earl R. Booth
Publisher:
ISBN:
Category : Flow visualization
Languages : en
Pages : 32
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Author: Jeffrey S. Zsoldos
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 814
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Author:
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ISBN:
Category :
Languages : en
Pages : 32
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Author:
Publisher:
ISBN:
Category : Astronautics
Languages : en
Pages : 230
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