Transonic Flutter Analysis Of Wing Based On Computational Fluid Dynamics

Nowadays, computing the subsonic and supersonic flutter problems in the frequency domainwith p-k or V-g methodologies is very conventional. Those computations are always based on alinearized unsteady potential flow hypothesis. However, in the transonic speed range, while theairflow becomes strongly compressive and the shocks occur over wings and bodies, the linear theoryis no longer available. As a result, the traditional methods are not proper for solving transonic flutterproblems.To calculate the transonic flow accurately, the Euler fluid governing equation is taken intoaccount. The semi-discrete approximation scheme is used for spatial discretization and the dual timestepping explicit multistage scheme is applied to temporal discretization. The moving mesh calculateswith the spring method, and the geometric conservation law is enforced to predict the volumes. Withall those details considered, the illustrated ONERA M6wing’s transonic aerodynamic loaddistribution fits NASA’s wind tunnel experiments perfectly.This paper’s motivation is to figure out the transonic flutter problems with the CFD basedfluid-structure interaction method. To solve the matrix equation of linear structural dynamics, themode superposition method, Newmark integration method and HHT integration method areintroduced. As to the fluid-structure coupling platform, the IPS is used to exchange data between thefluid and structure fields; both the parallel and serial algorithms are proposed as the fluid-structurestaggered time schemes. This dissertation calculates the transonic flutter issues withMFX(Multi-Fields Solver),which is constructed with ANSYS and CFX. Results of standard AGARD445.6wing this dissertation computed correspond with NASA’s wind tunnel experiments, and the“transonic dip” of another wing which has a simple missile also agrees with a foreign paper. Thatindicates the CFD based fluid-structure interaction method is reliable in predicting wing’s transonicflutter boundary.