Control of the Flow over a Delta Wing in the Transonic Regime

Riou, Jacques; Garnier, Éric; Basdevant, C.

doi:10.2514/1.j050531

Cited by 4 publications

(2 citation statements)

References 9 publications

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“…They reported that the spanwise nozzles located on the wing controlled the shock-induced separations. Riou et al [24] investigated efficacy of a suction slot on a leeward side of a 65 • swept wing and reported that the cross flow shock are altered due to the suction. Several other researchers investigated mechanical and fluidic vortex generators (VG) [25][26][27] on a transonic aerofoil wing and reported that the VG's were effective in controlling the shock-induced separation.…”

Section: Introductionmentioning

confidence: 99%

Control of shock-induced vortex breakdown on a delta-wing-body configuration in the transonic regime

2021

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Shock-induced vortex breakdown, which occurs on the delta wings at transonic speed, causes a sudden and significant change in the aerodynamic coefficients at a moderate angle-of-attack. Wind-tunnel tests show a sudden jump in the aerodynamic coefficients such as lift force, pitching moment and centre of pressure which affect the longitudinal stability and controllability of the vehicle. A pneumatic jet operated at sonic condition blown spanwise and along the vortex core over a 60° swept delta-wing-body configuration is found to be effective in postponing this phenomenon by energising the vortical structure, pushing the vortex breakdown location downstream. The study reports that a modest level of spanwise blowing enhances the lift by about 6 to 9% and lift-to-drag ratio by about 4 to 9%, depending on the free-stream transonic Mach number, and extends the usable angle-of-attack range by 2°. The blowing is found to reduce the magnitude of unsteady pressure fluctuations by 8% to 20% in the aft portion of the wing, depending upon the method of blowing. Detailed investigations carried out on the location of blowing reveal that the blowing close to the apex of the wing maximises the benefits.

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Section: Introductionmentioning

confidence: 99%

Control of shock-induced vortex breakdown on a delta-wing-body configuration in the transonic regime

2021

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“…The agreement of the results with the existing experimental data was very satisfactory since, for example, the errors on the lift and drag coefficients were found equal to 3 and 1.3%, respectively. Furthermore, this hybrid Reynoldsaveraged Navier-Stokes/large-eddy simulation approach has been successfully applied to the study of compressibility effects on the vortical flow over a highly swept wing [13] and to its control [14]. The grid is composed of 21 10 6 points.…”

Section: Introductionmentioning

confidence: 99%