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

Shigeru Obayashi, Ing Tsau Chiu, Guru P. Guruswamy

Research output: Contribution to conferencePaper

7 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 anti-symmetric oscillatory motions of the control surfaces on the left and right wings are studied. The anti-symmetric case produces higher lift than the steady case with no deflection, and the unsteady symmetric case produces higher lift than the anti-symmetric 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
Pages555-565
Number of pages11
Publication statusPublished - 1993 Jan 1
Externally publishedYes
EventFlight Simulation and Technologies, 1993 - Monterey, United States
Duration: 1993 Aug 91993 Aug 11

Other

OtherFlight Simulation and Technologies, 1993
CountryUnited States
CityMonterey
Period93/8/993/8/11

ASJC Scopus subject areas

  • Engineering(all)

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    Obayashi, S., Chiu, I. T., & Guruswamy, G. P. (1993). Navier-stokes computations on full-span wing body configuration with oscillating control surfaces. 555-565. Paper presented at Flight Simulation and Technologies, 1993, Monterey, United States.