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Accession Number:
AD0612007
Title:
REPRESENTATION OF PROPELLER WAKES BY SYSTEMS OF FINITE CORE VORTICES.
Corporate Author:
CORNELL AERONAUTICAL LAB INC BUFFALO N Y
Report Date:
1965-02-01
Abstract:
The report discusses the development of a propeller wake model and computational procedure aimed at the determination of the spatial distribution of wake vorticity and the associated induced velocity distribution. Numerical calculations were made for a number of vortex-ring configurations corresponding to a hovering rotor at onehalf, one and two ring radii above the ground, as well as out-of-ground effect. Both unsteady and time-averaged velocities were computed at various points in the wake for several cases. A model is proposed for the wake flow of a rotor in steady forward flight. Instead of the vortexring representation, the tip vortices are represented by continuous finite-core vortices. For purposes of numerical calculation, the continuous vortex is approximated by short straight-line segments. This model will enable the calculation of the time-dependent wake-vortex configuration, within the limitations of practicable computing running time, in which the various vortex elements move under mutual influence according to the laws of vortex dynamics. Author
Descriptive Note:
Summary rept. for Feb 63-Dec 64,
Pages:
0074
Contract Number:
Nonr369100
File Size:
0.00MB
