Accession Number:

AD0643159

Title:

WAKES OF LIFTING PROPELLERS (ROTORS) IN GROUND EFFECT

Descriptive Note:

Final rept., Feb 1965-May 1966

Corporate Author:

CORNELL AERONAUTICAL LAB INC BUFFALO NY

Personal Author(s):

Report Date:

1966-11-01

Pagination or Media Count:

99.0

Abstract:

The report presents the development of a wake model for a lifting propeller rotor in ground effect and the computational procedure used to determine the spacial distribution of wake vorticity and the induced velocity field accompanying that vorticity distribution. Sample calculations for a two- bladed rotor were carried out on an IBM 7044 computer. Locations of wake vortical elements and the associated induced velocities at selected field points are presented for advance ratios of 0, 0.02, 0.05, and 0.10 for an HR ratio of rotor height above ground to rotor radius of 1.0. Also, a few results for a hovering case with HR 0.5 are presented. A calculated root-mean-square velocity map is compared with measured hovering data time averaged and good agreement is obtained in the outer half of the slipstream. The implications of computed results with respect to the flow field at a horizontal stabilizer or tail rotor are noted as examples of the use of the model. The wake vortex model used for these calculations is a distorted continuous helix emanating from each blade tip.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE