Circulation Control Airfoil Study: Progress Report No. 4
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Authors
Schmidt, Louis Vincent
Subjects
Airfoil
Circulation Control Airfoil
Coanda Sheet
Circulation Control Airfoil
Coanda Sheet
Advisors
Date of Issue
1977-11-21
Date
11/21/1977
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
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 (t/c = 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, k=0 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
Type
Technical Report
Description
Series/Report No
Department
Identifiers
NPS Report Number
NPS-67SX-77111
Sponsors
Supported by the Naval Air Systems Command,
Washington, DC and David W. Taylor Naval Ship Research and Development
Center, Bethesda, MD.
Funder
a) NOOO19-77-WR-71012
b) NOO16-77-WR-0218
Format
NA
Citation
Distribution Statement
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.