by National Aeronautics and Space Administration, Ames Research Center, U.S. Army Aviation Systems Command in Moffett Field, Calif, St. Louis, Mo .
Written in English
|Other titles||Full potential modeling of blade-vortex interactions.|
|Statement||H.E. Jones, F.X. Caradonna.|
|Series||NASA technical memorandum -- 88355., USAAVSCOM technical memorandum -- 86-A-5., AVSCOM technical memorandum -- 86-A-5.|
|Contributions||Caradonna, F. X., Ames Research Center., United States. Army Aviation Systems Command.|
|The Physical Object|
Get this from a library! Full-potential modeling of blade-vortex interactions. [Henry E Jones; Langley Research Center.]. Get this from a library! Full-potential modeling of blade-vortex interactions. [Henry Edward Jones; F X Caradonna; Ames Research Center.; United States. Army Aviation Systems Command.]. full-potential modeling blade-vortex interaction vortex passage rotational flow mass conservation equation fl ow fi eld shock wave physical model vortex axis inviscid fl ow fl ow twodimensional potential flow field time-varying surface pressure aerodynamic problem airfoi boundary layer. Full potential modeling of blade-vortex interactions. By F. X. Caradonna and H. E. Jones. Abstract. A comparison is made of four different models for predicting the unsteady loading induced by a vortex passing close to an airfoil. (1) The first model approximates the vortex effect as a change in the airfoil angle of attack. (2) The second.
Full-Potential Modeling of Blade-Vortex Interactions. By Henry Jones and Henry E. Jones. Abstract. this report. Physical Model The solution of HSI requires the computation of the time-varying surface pressures during the vortex passage. Because the angle between the vortex axis and the blade is zero, no spanwise flows are i nduced and the. Full-Potential Modeling of Blade- Vortex Interactions H.E. Jones and F.X. Caradonna (hBSA -TPI-8 8 35 5) ELADE-VORTEX INIEPACTICNS (FPA) 30 p E UZL- ECT E hT 1 A2 MC DELI NG OE N CSCL 01s Unclas G3/01 August National Aeronautics and Space Administration United States Army Aviation Systems Command. A Consistent Approach for Modeling the Aerodynamics of Self‐Generated Rotor Blade‐Vortex Interactions Journal of the American Helicopter Society, Vol. 41, No. 2 Numerical simulation of the fuselage-rotor interaction phenomenon. Typical time signatures and frequency spectra of blade–vortex interaction noise in a far field are shown in Fig. 2, in which distinctive pulse shapes are noise signatures show several interactions and each consists of positive and negative amplitudes, with positive amplitudes dominant on the advancing side and negative amplitudes on the retreating side.
A study of tile full-potential modeling of a blade-vortex interaction was made. A primary goal of this study was to investigate tile effectiveness of the various methods of modeling the vortex. Tile problem was within the context of a two-di me nsional model problem, which represents one of. A blade vortex interaction (BVI) is an unsteady phenomenon of three-dimensional nature, which occurs when a rotor blade passes within a close proximity of the shed tip vortices from a previous blade. The aerodynamic interactions represent an important topic of investigation in rotorcraft research field due to the adverse influence produced on rotor noise, particularly in low speed descending. Interaction of a vortex, or combinations of them, with a cylinder, blade, or foil may involve both rapid distortion of the incident vorticity field and shedding of vorticity from the surface of the body. This review focuses on the underlying flow physics, with the aim of clarifying the origin of the induced loading. In the case of near or direct encounter of the incident vortex, the relation. Blade-Wake Interaction Noise for Turbines With Downwind Rotors J. Sol. Energy Eng (November, ) A Correlation-Based Transition Model Using Local Variables—Part II: Test Cases and Industrial Applications.