Navier-Stokes computations on full wing-body configuration with oscillating control surfaces

Shigeru Obayashi, Ing Tsau Chiu, Guru P. Guruswamy

Research output: Contribution to journalArticle

4 Citations (Scopus)

Abstract

Unsteady Navier-Stokes simulations have been performed for vortical flows over an “arrow-wing” configuration of a supersonic transport in the transonic regime. Computed steady pressures and integrated force coefficients with and without control surface deflection at a moderate angle of attack are compared with experiment. For unsteady cases, oscillating trailing-edge control surfaces are modeled by using moving grids. Response characteristics between symmetric and antisymmetric oscillatory motions of the control surfaces on the left and right wings are studied. The antisymmetric case produces higher lift than the steady case with no deflection and the unsteady symmetric case produces higher lift than the antisymmetric case. The detailed analysis of the wake structure revealed a strong interaction between the primary vortex and the wake vortex sheet from the flap region when the flap is deflected up.

Original languageEnglish
Pages (from-to)1227-1233
Number of pages7
JournalJournal of Aircraft
Volume32
Issue number6
DOIs
Publication statusPublished - 1995 Jan 1

ASJC Scopus subject areas

  • Aerospace Engineering

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