The Unsteady Behavior of Subsonic Wind Tunnel Wall Pressure during a Pitching Motion of the Model


1 Department of Mechanical and Aerospace Engineering, Islamic Azad University- Science and Research Branch, Poonak, Tehran, Iran

2 Department of Aerospace Engineering, Sharif University of Technology, Azadi Ave., Tehran, Iran

3 Department of Mechanical and Aerospace Engineering, Islamic Azad University-Science and Research Branch, Tehran, Iran


Extensive low speed wind tunnel experiments have been undertaken to measure the test section floor wall pressure distribution in presence of a 2D wing inside the test section. The experiments were performed for both static and dynamic pitching motion of the model at different conditions. In these measurements the effects of existence and oscillations of 2D wing on the floor wall pressure at various locations were studied. According to the results, as the oscillation parameters such as mean angle of attack and frequency change, the wall pressure at the points located in the front part of the test section, in the upstream region, exhibit a different behavior than those in the downstream part. Viscosity is shown to be a major contributor in convecting the fluctuations caused by the model oscillations to the flowfield. As the Reynolds number increases, the downstream region receives less disturbances from the pure dynamic motion of the model. It is believed that the static wake is the dominant contributor in the absence of the viscous effects.