NDLI: Calculation of helicopter rotor blade/vortex interaction by navier-stokes procedures

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Calculation of helicopter rotor blade/vortex interaction by navier-stokes procedures

Content Provider	NASA Technical Reports Server (NTRS)
Author	Shamroth, S. J. Buggeln, R. C. Kim, Y.-N.
Copyright Year	1987
Description	Interactions of a modern rotor blade with concentrated tip vortices from the previous blades can have a significant influence on the airloads and the aeroacoustics of a helicopter. A better understanding of the blade/vortex interaction process and a method of analyzing its flow field would provide valuable help in the design of helicopters. The work discussed herein represents an initial effort in applying a 3-D, time-dependent Navier-Stokes simulation to the blade vortex interaction problem. The numerical approach is the Linearized Block Implicit (LBI) technique. In this initial effort, consideration is given to the interaction of a wing of idealized geometry and a vortex whose axis is aligned at an arbitrary angle to the wing. The calculations are made for laminar, subsonic flow, and show the time dependent pressure distribution and flow fields resulting from the interaction.
File Size	1483952
Page Count	38
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19880003909
Archival Resource Key	ark:/13960/t8kd6sk19
Language	English
Publisher Date	1987-04-01
Access Restriction	Open
Subject Keyword	Aerodynamics Blade Tips Helicopters Rotors Blade-vortex Interaction Pressure Distribution Dimensions Navier-stokes Equation Geometry Time Dependence Wings Laminar Flow Computation Subsonic Flow Flow Distribution Helicopter Design Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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