Comparison of Two Shock-Capturing Methods for Calculation of Transonic Airfoil Flutter.
Abstract
The flutter of a pitch-and-plunge airfoil (PAPA) in transonic flow is simulated using two shock-capturing methods. Each method solves a coupled system of equations involving the unsteady Euler equations and a two-degree-of-freedom structural model. The first method, TVDntiAE, uses an explicit Total-Variation-Diminishing (TVD) algorithm to compute the flowfield for a 2-D airfoil. The second method, ENS3DAE, uses an implicit Beam-Warming approach to compute the flowfleld on a 3-D rectangular wing while enforcing 2-D flow. Results of the schemes are compared with each other and against limited published data to extend the validation of the software to unsteady fluid/structure interactions. Results are compared for three airfoil configurations: (1) static; (2) forced oscillation; and (3) PAPA. Computation of flutter points is of special interest. ENS3DAE predicts a flutter onset speed for the NACA 64A-006 airfoil at M=0.87 that is 1% greater than the value predicted by TVDntiAE and 2% smaller than the published data. Variations in model predictions most likely due to dissipation-model differences and grid and time-step sensitivities are evaluated. (AN)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1995
- Accession Number
- ADA302254
Entities
People
- Bradley J. Buxton
Organizations
- Air Force Institute of Technology