Experimental investigation of a slender delta wing with apex and tail flap control
Abstract eng: An experimental investigation of a slender delta wing with a sweeping angle Λ=65° was conducted with apex and tail flap control at a Reynolds number Re = 12,900. Dye flow visualization revealed the flow pattern and vortex breakdown (VBD) location over the different wing configurations. The flow visualization showed that a tail flap with anhedral deflection angle of -15° (T-15) or -30° (T-30) promoted VBD while a tail flap with dihedral deflection angle of +15° (T+15) or +30° (T+30) delayed VBD. A combination of apex flap -15° and tail +30° (A15/T+30) delayed VBD the most of all the cases. A particle image velocimetry (PIV) study was conducted to characterize the flow.
Publisher:
International Union of Theoretical and Applied Mechanics, 2016
Conference Title:
Conference Title:
24th International Congress of Theoretical and Applied Mechanics
Conference Venue:
Montreal (CA)
Conference Dates:
2016-08-21 / 2016-08-26
Rights:
Text je chráněný podle autorského zákona č. 121/2000 Sb.
Record appears in:
Record created 2016-11-15, last modified 2016-11-15
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