Unsteady pressure and structural response measurements on an elastic supercritical wingResults are presented which define unsteady flow conditions associated with high dynamic response experienced on a high aspect ratio elastic supercritical wing at transonic test conditions while being tested in the NASA Langley Transonic Dynamics Tunnel. The supercritical wing, designed for a cruise Mach number of 0.80, experienced the high dynamic response in the Mach number range from 0.90 to 0.94 with the maximum response occurring at a Mach number of approximately 0.92. At the maximum wing response condition the forcing function appears to be the oscillatory chordwise movement of strong shocks located on both the wing upper and lower surfaces in conjuction with the flow separating and reattaching in the trailing edge region.
Document ID
19880045004
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Eckstrom, Clinton V. (NASA Langley Research Center Hampton, VA, United States)
Seidel, David A. (NASA Langley Research Center Hampton, VA, United States)
Sandford, Maynard C. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1988
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 88-2277
Meeting Information
Meeting: Structures, Structural Dynamics and Materials Conference