Accession Number:

ADA048677

Title:

Circulation Control Airfoil Study.

Descriptive Note:

Progress rept. no. 4, Jan-Nov 77,

Corporate Author:

NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF

Personal Author(s):

Report Date:

1977-11-21

Pagination or Media Count:

30.0

Abstract:

The prime goal of the investigations has been the evaluation of the unsteady aerodynamics, and in particular the transfer functions, applicable to the Circulation Control Airfoil CCA for the situation of harmonic blowing perturbations superimposed upon a mean cavity pressure. Circulation control was achieved upon the relatively thick tc 0.214 elliptically shaped two-dimensional air foil by tangential jet injection at an upper surface slot just ahead of the rounded trailing edge. The experiments were conducted in the Naval Postgraduate School unsteady flow 2 x 2 foot wind tunnel. Preliminary results were obtained disclosing the nature of unsteady surface pressures over the airfoil, both amplitude and phase, relative to the oscillating cavity pressures for a range of reduced frequencies, k0 to 0.46, at a model attitude approximating the zero lift condition blowing-off at a moderate value of momentum blowing coefficient. Positive results were obtained towards identifying the behavior of the Coanda sheet dynamics, airfoil lift transfer function and airfoil damping moment.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE