Accession Number:

ADA254323

Title:

Nonlinear Stall Flutter of Wings With Bending-Torsion Coupling

Descriptive Note:

Final technical rept. 1 Feb-31 Oct 1991,

Corporate Author:

MASSACHUSETTS INST OF TECH CAMBRIDGE TECHNOLOGY LAB FOR ADVANCED COMPOSITES

Personal Author(s):

Report Date:

1991-12-31

Pagination or Media Count:

286.0

Abstract:

The nonlinear, stalled, aeroelastic behavior of rectangular. graphiteepoxy, cantilevered plates with varying amounts of bending-torsion stiffness coupling and with NACA 0012 Styrofoam airfoil shapes is investigated for low Reynolds number flow 200,000. A general Rayleigh-Ritz formulation is used to calculate point load static deflections, and nonlinear static vibration frequencies and mode shapes for varying tip deflections. Nonlinear lift and moment aerodynamics are used in the context of the Rayleigh-Ritz formulation to calculate static airload deflections. The nonlinear, stalled ONERA model using non-constant coefficients - initially developed by Tran and Petot - is reformulated into a harmonic balance form and compared against a time-marching Runge-Kutta scheme. Low angle-of-attack, linear flutter calculations are done by applying Fourier analysis to extract the harmonic balance method and a Newton- Raphson solver to the resulting nonlinear. Rayleigh-Ritz aeroelastic formulation. Nonlinear flutter, Stall flutter, Composites Aeroelasticity.

Subject Categories:

  • Aircraft
  • Laminates and Composite Materials
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE