Time-Accurate Aeroelastic Computations of a Full Helicopter Model using the Navier-Stokes Equations

Abstract

A time-accurate procedure to model fluid/structure interactions of helicopter blades is presented. The Navier-Stokes equations in conjunction with the one-equation SpalartAllmaras turbulence model are used to compute the flow. Structural dynamics is modeled using the modal equations. The aerodynamic and structural dynamic equations are coupled time-accurately using the linear acceleration method of Newmark (direct integration scheme). Effects of time accuracy on the computed results are investigated. Results are compared with experimental data for a full rotor blade system.

Navier–Stokes Equations-Based Aeroelasticity of Supersonic Transport Including Short-Period Oscillations

“…In this work, Eq. 3is solved using Newmark's time integration method in association with the instantaneous Lagrangian-Eulerian approach (also known as arbitrary Lagrangian-Eulerian) [12], with the aerodynamic data computed by solving the RANS equations [13]. For this work, the RANS equations are numerically solved using the OVERFLOW code [14], which uses the diagonal form of the Beam-Warming central difference algorithm [15], along with the one-equation Spalart-Allmaras turbulence model [16].…”

Time-Accurate Coupling of Three-Degree-of-Freedom Parachute System with Navier–Stokes Equations

“…Equation 1is solved using Newmark's time-integration method in association with the instantaneous Lagrangian-Eulerian approach (known as arbitrary Lagrangian-Eulerian) [14], with the aerodynamic data F A and F N computed by solving RANS equations [15]. For this work, the RANS equations are numerically solved using the diagonal form of the Beam-Warming central-difference algorithm [16], along with the one-equation Spalart-Allmaras turbulence model [17].…”

“…Using these loads, Eq. (1) is integrated in a module outside the CFD code using Newmark's time-integration method, as described in [14]. Integration is started with an initial nondimensional velocity of 0.01.…”

Frequency Domain Flutter Boundary Computations Using Navier-Stokes Equations on Superclusters

“…A factor-of-10 increase in the problem size needed only a 4% increase in the wall-clock time. The present procedure can be extended to complex geometries such as full-rotorcraft following the timeintegration procedure presented in [13].…”