Accession Number : ADA332264
Title : Design and Development of a Dynamically Deforming Leading Edge Airfoil for Unsteady Flow Control.
Descriptive Note : Conference paper,
Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA DEPT OF AERONAUTICS AND ASTRONAUTICS
Personal Author(s) : Chandrasekhara, M. S. ; Carr, L. W. ; Wilder, M. C. ; Paulson, G. N. ; Sticht, C. D.
PDF Url : ADA332264
Report Date : OCT 1997
Pagination or Media Count : 10
Abstract : A novel approach to unsteady flow separation and dynamic stall control using a dynamically deforming leading edge airfoil is described. The design details of a carbon-fiber composite skin airfoil having a thickness of 0.002 in. at the leading edge and capable of deforming at 20 Hz in unsteady flow at freestream Mach numbers of up to 0.45, are discussed. Implementation of the scheme at model scales places extraordinary demands on the design, material and fabrication of such an airfoil. Rate scaling further requires very-rapid-response instrumentation, measurement techniques and data acquisition schemes. The special instrumentation control system developed for these experiments as well as the fluid dynamic results of successful flow control that was achieved using this method, are also discussed.
Descriptors : *COMPOSITE MATERIALS, *AIRFOILS, *FLOW SEPARATION, *AIRCRAFT DESIGN, CONTROL SYSTEMS, INSTRUMENTATION, LEADING EDGES, UNSTEADY FLOW, FLUID DYNAMICS.
Subject Categories : Aerodynamics
Distribution Statement : APPROVED FOR PUBLIC RELEASE