Contrasting the Harmonic Balance and Linearized Methods for Oscillating-Flap Simulations

In the framework of unsteady aerodynamics, forced-harmonic-motion simulations can be used to compute unsteady loads. In this context, the present paper assesses two alternatives to the unsteady Reynolds-averaged Navier–Stokes approach, the linearized unsteady Reynolds-averaged Navier–Stokes equations method, and the harmonic balance approach. The test case is a NACA 64A006 airfoil with an oscillating ␣ap mounted at 75% of the chord. Emphasis is put on examining the performances of the methods in terms of accuracy and computational cost over a range of physical conditions. It is found that, for a subsonic ␣ow, the linearized unsteady Reynolds-averaged Navier–Stokes method is the most ef␣cient one. In the transonic regime, the linearized unsteady Reynolds-averaged Navier–Stokes method remains the fastest approach, but with limited accuracy around shocks, whereas a one- harmonic harmonic balance solution is in closer agreement with the unsteady Reynolds-averaged Navier–Stokes solution. In the case of separation in the transonic regime, the linearized unsteady Reynolds-averaged Navier–Stokes method fails to converge, whereas the harmonic balance remains robust and accurate

Prediction of generalized aerodynamic forces following linearized supersonic theory

Contribution a : International forum on aeroelasticity and structural dynamics 1991, Aachen (Germany), June 3-6, 1991SIGLEAvailable at INIST (FR), Document Supply Service, under shelf-number : 22419, issue : a.1991 n.114 / INIST-CNRS - Institut de l'Information Scientifique et TechniqueFRFranc

Unsteady transonic wing nacelle interference for different oscillatory modes

Abstract. This paper presents results of the numerical part of the DLR-ONERA project WIONA (Wing with Oscillating Nacelle). Unsteady aerodynamics of a generic wingpylon- nacelle configuration is investigated and CFD simulation tools are validated with test results and against one another. The results show that for the present configuration unsteady aerodynamics for different forced oscillations, of the whole model as well as of pylon and nacelle alone, can be precisely predicted in transonic flow including shock induced separation

Prevision des forces aerodynamiques instationnaires en supersonique linearise

Contribution a : 27eme colloque d'aerodynamique appliquee, Marseille, 15-17 octobre 1990SIGLEAvailable at INIST (FR), Document Supply Service, under shelf-number : 22419, issue : a.1990 n.164 / INIST-CNRS - Institut de l'Information Scientifique et TechniqueFRFranc

Transonic aeroelastic computations using Navier-Stokes equations

Communication to : International forum on aeroelasticity and structural dynamics (IFASD 2003), Amsterdam (Pays-Bas), June 04-06, 2003SIGLEAvailable from INIST (FR), Document Supply Service, under shelf-number : 22419 / INIST-CNRS - Institut de l'Information Scientifique et TechniqueFRFranc

Velocity measurements in hypersonic flows

Communication to : 9th international symposium of unsteady, Lyon (France), September 04-07, 2000SIGLEAvailable from INIST (FR), Document Supply Service, under shelf-number : 22419, issue : a.2000 n.167 / INIST-CNRS - Institut de l'Information Scientifique et TechniqueFRFranc