Aerodynamic Interference Effects on Oscillating Airfoils with Controls in Ventilated Wind Tunnels

Fromme, J. A.; Golberg, Michael A.

doi:10.2514/3.50774

Cited by 9 publications

(2 citation statements)

References 14 publications

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“…When the model oscillates inside a wind tunnel test section, it can communicate with the test section wall through the oscillatory air around it. Interference effects can be corrected using contemporarily experimental and computational methods 23–28 . Dynamic tests in both pitching and plunging motions on three‐dimensional models were conducted and the wall interference effects were obtained by Beyers 29 and Davari and Soltani 30 in recent years based on the experimental wind tunnel wall pressure distribution.…”

Section: Introductionmentioning

confidence: 99%

Experimental Study of the Plunging Motion with Unsteady Wind Tunnel Wall Interference Effects

Soltani

Marzabadi

Mohammadi

2011

Experimental Techniques

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A series of experiments were carried out to investigate unsteady behavior of the flow field as well as the boundary layer of an airfoil oscillating in plunging‐type motion in a subsonic wind tunnel. The measurements involved surface‐mounted hot films complimented with surface pressure. In addition, wind tunnel wall pressure distribution was acquired to furnish a baseline for the wall interference corrections. The airfoil is the section of a 660‐kW wind turbine blade. The experiments were conducted at a Reynolds number of 0.42 million, and over two reduced frequencies of k = 0.06 and 0.085, at prestall, nearstall, and poststall regions. The unsteady aerodynamic loads were calculated from the surface pressure measurements, 64 ports, along the chord for both upper and lower surfaces of the model. The plunging displacements were transformed into the equivalent angle of attack. The surface hot‐film measurements provided information about the boundary‐layer events. The boundary‐layer transition occurred via a laminar separation bubble. Variations of the surface pressure coefficients and aerodynamic loads with the equivalent angle of attack showed strong sensitivity to the reduced frequency and the mean angles of attack. The wall pressure distribution was affected by the model oscillation especially the region underneath the model.

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Section: Introductionmentioning

confidence: 99%

Experimental Study of the Plunging Motion with Unsteady Wind Tunnel Wall Interference Effects

Soltani

Marzabadi

Mohammadi

2011

Experimental Techniques

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“…This effect was also observed in wind tunnel tests on oscillating models. Frornrne and Golberg [22] reformulated Possio's kernel for a 2D airfoil in order to include the boundary conditioins of wind tunnel walls and were able to compute the effects of wind tunnel wall resonance.…”

Section: Extension Of Possio's Methods After the Warmentioning

confidence: 99%

The Legacy of Camillo Possio to Unsteady Aerodynamics

Voß

IFIP International Federation for Information Processing

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First a brief overview is given of Camillo Possio's short but outstanding and fruitful career. This is followed by an outline of the state of the art in flutter and unsteady aerodynamic research, and the challenges and problems like high-speed flight that arose in aircraft development at that time. Possio's first publications on gas dynamic and supersonic problems are reviewed. The main focus is on the 1938 report on unsteady subsonic compressible 2D flow that became famous and was named after him, because he was the first person to developed an unsteady compressible aerodynamic theory, which was urgently needed in those years. The theory, which is based on Prandtl's acceleration potential is briefly outlined. Some discussions and comments that took place in Germany and other countries at that time highlight the importance of this work for the scientific community. Early solutions of Possio's integral equation developed by himself and later ones developed by other researchers are presented, as well as approaches that extended the theory to 3 dimensional flows before the war, like Kuessner's theory, which was probably influenced by Possio. Finally Carnillo Possio's later scientific contributions to wind tunnel interference and to hydrodynamics are described. A summary of some developments of the 2nd half of the 20th century demonstrate that Camillo Possio created a milestone for modern aircraft research during his very short career.

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Singular Integral Equations in Aerodynamics

Ladopoulos

2000

Singular Integral Equations

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Aerodynamic Interference Effects on Oscillating Airfoils with Controls in Ventilated Wind Tunnels

Cited by 9 publications

References 14 publications

Experimental Study of the Plunging Motion with Unsteady Wind Tunnel Wall Interference Effects

Experimental Study of the Plunging Motion with Unsteady Wind Tunnel Wall Interference Effects

The Legacy of Camillo Possio to Unsteady Aerodynamics

Singular Integral Equations in Aerodynamics

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