Time‐linearized time‐harmonic 3‐D Navier–Stokes shock‐capturing schemes

Chassaing, Jean-Camille; Gerolymos, G. A.

doi:10.1002/fld.1523

Cited by 5 publications

(3 citation statements)

References 100 publications

(247 reference statements)

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“…15 However, the frozen-turbulent eddy-viscosity approach is a common choice for many applications due to robustness issues encountered in the numerical solution process (Dufour 16 ). According to developments by Chassiang, 17 Pechloff and Laschka 18 used a limiting procedure for the turbulent transport variable as a stabilizing technique for the pseudo-time marching method and obtained good results for the NASA clipped delta wing with strong shocks. In conjunction with strong leading edge vortices that approach show relatively large deviations in comparison to URANS simulations.…”

Section: Introductionmentioning

confidence: 99%

Efficient Evaluation of Dynamic Response Data with a Linearized Frequency Domain Solver at Transonic Separated Flow Condition

Widhalm

Thormann

2017

35th AIAA Applied Aerodynamics Conference

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Each perturbation of an aircraft state in trim induces aerodynamic loads on wings, control surfaces and other parts of an aircraft. These loads have to be quantified for a wide range of flight states covering the flight envelope. Small disturbance approaches based on the Reynolds-averaged Navier Stokes equations fulfil the requirements of efficiently predicting accurate dynamic response data. These time-linearized methods have been successfully applied in flight dynamic and aeroelastic analyses for moderate flight conditions. Small disturbance approaches on the basis of Navier-Stokes solvers have become most often the right choice, for example in flight dynamic and aeroelastic analysis, to combine efficiency and accuracy for predicting dynamic response data. However, in complex flows exhibiting shock-induced separations, deficits in robustness of the iterative solution methods often lead to simplifications of the equations and thus reducing the quality of the computed results. The presented linearized frequency domain solver has shown accurate results compared to nonlinear time-accurate unsteady simulations for attached flow conditions. The area of application is extended to separated transonic flows demonstrating the method's capability to accurately capture strong shock-boundary interactions. Deriving the exact linearization of the turbulence model as well as implementing a robust method to solve the stiff linear systems are key tasks to achieve this target. Results are presented for the LANN wing undergoing rigid body motions comparing dynamic derivatives of lift and moment coefficients between the linearized frequency domain solver and its time-domain counterpart. In addition, local surface pressure and skin friction coefficients are analysed at two span stations. The presented linearized frequency domain solver (TAU-LFD) has shown accurate results in comparison to fully time-accurate unsteady simulations at separated transonic flow conditions.

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Section: Introductionmentioning

confidence: 99%

Efficient Evaluation of Dynamic Response Data with a Linearized Frequency Domain Solver at Transonic Separated Flow Condition

Widhalm

Thormann

2017

35th AIAA Applied Aerodynamics Conference

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“…This had also been the case in [4]. In the Chassaing and Gerolymos [7] recommendation, the destabilization of the derived linear equation system's solution would be most effectively countered by avoiding pseudotime integration altogether. This instance has been adopted by Petrie-Repar at the German Aerospace Center [9], directly applying a GMRES approach to the derived linear equation system.…”

Section: Introduction Tmentioning

confidence: 99%

“…Chassaing and Gerolymos provide a history of small disturbance Navier-Stokes methods, as well as their Euler predecessors, up to the year 2005 [7]. These are categorized by spatial dimension and discretization, the solution scheme, and (in case of the viscous methods) the employed turbulence model.…”

Section: Introduction Tmentioning

confidence: 99%

Small Disturbance Navier-Stokes Computations for Low-Aspect-Ratio Wing Pitching Oscillations

Pechloff

Laschka

2010

Journal of Aircraft

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For dynamic production aeroelastic analysis in the transonic speed range, a computational fluid dynamics method based on the small disturbance Navier-Stokes equations can serve as a reasonable alternative to one realizing the Reynolds-averaged Navier-Stokes equations' time-domain solution. Its dynamically linear approach promises a significantly decreased computation cost in the prediction of unsteady aerodynamic loading while retaining the latter's fidelity to a high degree. In this regard, research conducted at the Technical University of Munich has resulted in the computational fluid dynamics method FLM-SD.NS. Further substantiating its application readiness, harmonic pitching oscillations of the NASA clipped delta wing are investigated. Test cases are characterized by shocks of varying strengths and ranges of motion, as well as leading-edge vortex formation. Overall, results are in good agreement with dynamically fully nonlinear solutions provided by the comparative Reynolds-averaged NavierStokes solver FLM-NS, as well as available experimental data. Reductions in computation time, up to an order of magnitude, in relation to FLM-NS are observed. Limitations of the small disturbance approach, however, become apparent for the leading-edge vortex case, in which higher-order harmonics are far less negligible in the flow's response to the excitation.

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Time-harmonic Navier–Stokes computations of forced shock-wave oscillations in a transonic nozzle

et al. 2016

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Time‐linearized time‐harmonic 3‐D Navier–Stokes shock‐capturing schemes

Cited by 5 publications

References 100 publications

Efficient Evaluation of Dynamic Response Data with a Linearized Frequency Domain Solver at Transonic Separated Flow Condition

Efficient Evaluation of Dynamic Response Data with a Linearized Frequency Domain Solver at Transonic Separated Flow Condition

Small Disturbance Navier-Stokes Computations for Low-Aspect-Ratio Wing Pitching Oscillations

Time-harmonic Navier–Stokes computations of forced shock-wave oscillations in a transonic nozzle

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