Airfoil pressure measurements during a blade vortex interaction and a comparison with theory

Straus, Joe M.; Renzoni, P.; Mayle, R. E.

doi:10.2514/3.10378

Cited by 38 publications

(28 citation statements)

References 12 publications

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“…It was important to keep the time of the pitching motion less than the time for the air to travel one chord of the pitching airfoil. 19 In the current study, the chord of the vortex generator was 0.3 m with a response time of 25-30 ms, which was limited by the speed of the actuator. Therefore, the maximum freestream velocity allowed was 0.3 m/0.03 s = 10 m/s.…”

Section: B Vortex Generation Systemmentioning

confidence: 92%

Vortex dynamics during blade-vortex interactions

Peng

Gregory

2015

Physics of Fluids

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Articles you may be interested inAdvance ratio effects on the flow structure and unsteadiness of the dynamic-stall vortex of a rotating blade in steady forward flight Phys. Fluids 27, 027101 (2015); 10.1063/1.4906803 Effect of a splitter plate on the dynamics of a vortex pair Phys. Fluids 24, 074110 (2012); 10.1063/1.4737878Evaluation of active flow control applied to wind turbine blade section Vortex dynamics during parallel blade-vortex interactions (BVIs) were investigated in a subsonic wind tunnel using particle image velocimetry (PIV). Vortices were generated by applying a rapid pitch-up motion to an airfoil through a pneumatic system, and the subsequent interactions with a downstream, unloaded target airfoil were studied. The blade-vortex interactions may be classified into three categories in terms of vortex behavior: close interaction, very close interaction, and collision. For each type of interaction, the vortex trajectory and strength variation were obtained from phase-averaged PIV data. The PIV results revealed the mechanisms of vortex decay and the effects of several key parameters on vortex dynamics, including separation distance (h/c), Reynolds number, and vortex sense. Generally, BVI has two main stages: interaction between vortex and leading edge (vortex-LE interaction) and interaction between vortex and boundary layer (vortex-BL interaction). Vortex-LE interaction, with its small separation distance, is dominated by inviscid decay of vortex strength due to pressure gradients near the leading edge. Therefore, the decay rate is determined by separation distance and vortex strength, but it is relatively insensitive to Reynolds number. Vortex-LE interaction will become a viscous-type interaction if there is enough separation distance. Vortex-BL interaction is inherently dominated by viscous effects, so the decay rate is dependent on Reynolds number. Vortex sense also has great impact on vortex-BL interaction because it changes the velocity field and shear stress near the surface. C 2015 AIP Publishing LLC.

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Section: B Vortex Generation Systemmentioning

confidence: 92%

Vortex dynamics during blade-vortex interactions

Peng

Gregory

2015

Physics of Fluids

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“…Figure 2.15: Schematic of the Configuration Employed in the Experiment Conducted by Kitaplioglu and Caradonna (1994) Figure 2.16: Acoustic Results for a Two-Bladed Rotor (Experimental and Numerical) for a) a Parallel Interaction, and b) an Oblique Interaction (Kitaplioglu and Caradonna, 1994) Figure 2.17: Schematic for the Numerical Shock Tube Employed by Mamou et al (2001) Straus et al (1990) and Discrete Vortex Method Data (Solid Line) Obtained by Renzoni (1987) Figure 5.21: Lift Coefficient for Domain A Simulation (red line), Straus et al 's (1990) Experimental Data (blue +) and Renzoni's (1987) Obtained by Measurements at Re v = 50,000 (Leishman, 2006) 233…”

Section: Abstract IIImentioning

confidence: 99%

“…The methods invoked to recreate the vortex in wind tunnels vary from moving airfoils (pitching (Straus et al, 1990;Kalkhoran and Wilson. 1992;and Seath et al, 1989) or oscillating (Booth and Yu, 1986;and Booth and Yu, 1990)) to stationary airfoils (shock tube (Lee and Bershader, 1994) or blade tip (Caradonna and Strawn, 1988)) at some distance upstream of the test airfoil.…”

Section: Experimental Investigations In Blade (Airfoil)-vortex Interactionmentioning

confidence: 99%

“…The vortex is then allowed to convect downstream as occurs in numerical simulations. Experimental investigations in both the subsonic (Seath et al, 1989;Lee and Bershader, 1994;Straus et al, 1990;Kalkhoran and Wilson, 1992;Booth and Yu, 1986;Caradonna and Strawn, 1988;and Booth and Yu, 1990) and transonic (Kalkhoran and Wilson, 1992;and Caradonna and Strawn, 1988) flow regimes have been performed. Experimental work mainly exploits the 2D nature of the parallel BVI measure since it is a simpler event to measure.…”

Section: Experimental Investigations In Blade (Airfoil)-vortex Interactionmentioning

confidence: 99%

“…The effects of the maximum pitch angle on the resulting vortex as well as that of the vortex position and freestream velocity were also included in this investigation. Straus et al (1990) pitched a NACA 0018 airfoil to create a vortex which was then measured with hot-wire anemometry. It was determined that inviscid theory accurately only predicts the pressure distribution on the test airfoil for specific situations.…”

Section: Experimental Investigations In Blade (Airfoil)-vortex Interactionmentioning

confidence: 99%

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