Finite-Wing and Sweep Effects on Transonic Buffet Behavior
نویسندگان
چکیده
This study experimentally investigates the effects of sweep angle and finite wing on transonic buffet, studying two-dimensional (2-D) three-dimensional configurations. Background-oriented schlieren stereographic particle image velocimetry (PIV) have been used as measurement techniques, performing experiments an OAT15A airfoil (clamped to both side windows wind tunnel), unswept wing, two swept wings with angles 15 30 deg, respectively. The three are also based clamped at tunnel only their root (free wingtip). All tested a constant normal Mach number ([Formula: see text]) respect leading edge. results show that buffet oscillations much stronger for than finite-span wings. A large difference in behavior can be noticed between is seen oil flow visualizations. particularly evident correspondence more outboard spanwise locations, suggesting important role could played by finite-wing effects: notably, tip vortex. spectral analysis has shown wings, classical 2-D peak (occurring [Formula: text] present conditions) substantially attenuated, whereas additional contributions range 450–850 Hz appear. PIV showed, deg periodical occurrence secondary supersonic area downstream main shock wave structure, which absent other models. configuration allowed reconstruction spanwise-oriented velocity component, obtaining, proximity trailing-edge, values component agreement convection cells observed literature this region.
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ژورنال
عنوان ژورنال: AIAA Journal
سال: 2022
ISSN: ['0001-1452', '1533-385X', '1081-0102']
DOI: https://doi.org/10.2514/1.j061974