Numerical prediction of the aerodynamic behaviour of porous airfoils

Savu, G.; Trifu, O.

doi:10.1007/bfb0041849

Cited by 1 publication

(2 citation statements)

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“…The facility comprises the following components as presented in Figure 5: a wind tunnel duct, air inlet and inlet honeycomb (1); Schlieren optics system (2); measuring section with optical access by two 11 cm quartz windows (3); control panel with a safety shut down button and manometer (4); fan (5); switch power supply cabinet (6); digital scanning valve for pressure profile along the bottom wall of the wind tunnel (7). The provided Schlieren optics, in conjunction with a high-speed camera, enable the direct observation of flow and the resulting shock phenomena.…”

Section: Experimental Facilitymentioning

confidence: 99%

“…Moreover, the shock system might strongly interact with the boundary layer leading to larger viscous dissipation. Shock and boundary layer active or passive control methods [1], including vortex generators [2,3], single or double slots, bumps [4] and perforated strips [5][6][7][8], have been investigated throughout the years to mitigate the detrimental effects of shock-induced phenomena.…”

Section: Introductionmentioning

confidence: 99%

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Effects of Perforated Plates on Shock Structure Alteration for NACA0012 Airfoils

Gall,

Dumitrescu,

Drăgan

et al. 2024

Inventions

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This research investigated a passive flow control technique to mitigate the adverse effects of shock wave–boundary layer interaction on a NACA 0012 airfoil. A perforated plate with a strategically positioned cavity beneath the shock wave anchoring spot was employed. Airfoils with perforated plates of varying orifice sizes (ranging from 0.5 to 1.2 mm) were constructed using various manufacturing techniques. Experimental analysis utilized an “Eiffel”-type open wind tunnel and a Z-type Schlieren system for flow visualization, along with static pressure measurements obtained from the bottom wall. Empirical observations were compared with steady 3D density-based numerical simulations conducted in Ansys FLUENT for comprehensive analysis and validation. The implementation of the perforated plate induced a significant alteration in shock structure, transforming it from a strong normal shock wave into a large lambda-type shock. The passive control case exhibited a 0.2% improvement in total pressure loss and attributed to the perforated plate’s capability to diminish the intensity of the shock wave anchored above. Significant fluctuations in shear stress were introduced by the perforated plate, with lower stress observed in the plate area due to flow detachment from cavity blowing. Balancing shock and viscous losses proved crucial for achieving a favorable outcome with this passive flow control method.

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Section: Experimental Facilitymentioning

confidence: 99%