RECENT ADVANCES IN TRANSONIC COMPUTATIONAL AEROELASTICITY

Abstract

A transonic unsteady aerodynamic and aeroelasticity code called CAP–TSD has been developed for application to realistic aircraft configurations. The code permits the calculation of steady and unsteady flows about complete aircraft configurations for aeroelastic analysis in the flutter critical transonic speed range. The CAP–TSD code uses a time-accurate approximate factorization (AF) algorithm for solution of the unsteady transonic small-disturbance potential equation. The paper gives an overview of the CAP–TSD code development effort and presents results which demonstrate various capabilities of the code. Calculations are presented for several configurations including the General Dynamics one-ninth scale F-16C aircraft model and the ONERA M6 wing. Calculations are also presented from a flutter analysis of a 45° sweptback wing which agree well with the experimental data. The paper presents descriptions of the CAP–TSD code and algorithm details along with results and comparisons which demonstrate these recent developments in transonic computational aeroelasticity.