A Computational Framework for Helicopter Fuselage Drag Reduction Using Vortex Generators
| Autor: | Jean-Christophe Boniface |
|---|---|
| Přispěvatelé: | ONERA - The French Aerospace Lab [Meudon], ONERA-Université Paris Saclay (COmUE) |
| Rok vydání: | 2016 |
| Předmět: |
0209 industrial biotechnology
GENERATEUR TOURBILLON HELICOPTER 02 engineering and technology Vortex generator Computational fluid dynamics Boundary layer thickness 01 natural sciences [SPI.MECA.MEFL]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Fluids mechanics [physics.class-ph] 010305 fluids & plasmas Physics::Fluid Dynamics 020901 industrial engineering & automation METHODE CHIMERE 0103 physical sciences Aerospace engineering HELICOPTERE Physics DRAG REDUCTION business.industry Static pressure Mechanics REDUCTION TRAINEE COMPUTATIONAL FLUID DYNAMICS Flow control (fluid) Boundary layer CHIMERA METHOD Fuselage Drag MECANIQUE FLUIDE NUMERIQUE business VORTEX GENERATOR |
| Zdroj: | Journal-American Helicopter Society Journal-American Helicopter Society, American Helicopter Society Inc, 2016, ⟨10.4050/JAHS.61.032002⟩ |
| ISSN: | 2161-6027 0002-8711 |
| DOI: | 10.4050/jahs.61.032002 |
| Popis: | International audience; A computational framework is described for the computational fluid dynamics (CFD) simulation of a bluff helicopter fuselage equipped with vortex generators (VGs). The VGs are explicitly discretized in the CFD mesh, using an overset grid method. A computational setup was developed allowing parametric investigations for VG size, pitch angle, position, number, arrangement, and thickness effects. High-density meshes were generated with successive grid overlap between body-fittedmeshes with high grid resolution in the boundary layer and Cartesian grids for the near and far field. The methodology was applied to the model-scale GOAHEAD model with sponsons. This model permits drag reduction by passive flow control on the model back ramp where the pronounced upsweep is responsible for a large separated flow at the backdoor/tail-boom junction. A test matrix was completed, and a VG layout proved its effectiveness for an eight-pair array of counterrotatingzero-thickness vane-type VGs, with the device height defined according to the local boundary layer thickness. At cruise conditions, some VG configurations tested achieve up to 5% drag reduction by cumulated effects of flow reattachment, limited device drag, and static pressure recovery. |
| Databáze: | OpenAIRE |
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