NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Forced Rolling Oscillation of a 65 deg-Delta Wing in Transonic Vortex-Breakdown FlowUnsteady, transonic, vortex dominated flow over a 65 deg. sharp-edged, cropped-delta wing of zero thickness undergoing forced rolling oscillations is investigated computationally. The wing angle of attack is 20 deg. and the free stream Mach number and Reynolds number are 0.85 and 3.23 x 10(exp 6), respectively. The initial condition of the flow is characterized by a transverse terminating shock which induces vortex breakdown of the leading edge vortex cores. The computational investigation uses the time accurate solution of the laminar, unsteady, compressible, full Navier-Stokes equations with the implicit, upwind, Roe flux difference splitting, finite-volume scheme. While the maximum roll amplitude is kept constant at 4.0 deg., both Reynolds number and roll frequency are varied covering three cases of forced sinusoidal rolling. First, the Reynolds number is held at 3.23 x 10(exp 6) and the wing is forced to oscillate in roll around the axis of geometric symmetry at a reduced frequency of 2(pi). Second, the Reynolds number is reduced to 0.5 x 10(exp 6) to observe the effects of added viscosity on the vortex breakdown. Third, with the Reynolds number held at 0.5 x 10(exp 6), the roll frequency is reduced to 1(pi) to complete the study.
Document ID
19960020979
Document Type
Conference Paper
Authors
Menzies, Margaret A. (Old Dominion Univ. Norfolk, VA United States)
Kandil, Osama A. (Old Dominion Univ. Norfolk, VA United States)
Kandil, Hamdy A. (Old Dominion Univ. Norfolk, VA United States)
Date Acquired
August 17, 2013
Publication Date
February 1, 1996
Publication Information
Publication: Aeroelastic, CFD, and Dynamic Computation and Optimization for Buffet and Flutter Applications
Subject Category
Aerodynamics
Report/Patent Number
AIAA Paper 95-1771-CP
Meeting Information
13th AIAA Applied Aerodynamics Conference(Sheraton Harbor, CA)
Distribution Limits
Public
Copyright
Public Use Permitted.
Document Inquiry