The instantaneous vortex structure of the leading-edge vortices on a delta wing in unsteady free stream is investigated via particle image velocimetry in unsteady wind tunnel of NUAA.

A pitching test set-up, used in the unsteady wind tunnel at Nanjing University of Aeronautics & Astronautics, is developed to study the effect of rapid changes on both the free stream velocity and the angle of attack.

In this paper, the effects of unsteady free stream on aerodynamics of an aircraft model are studied in the unsteady wind tunnel of NUAA.

Wind engineering and atmospheric boundary layer wind tunnel;

FEM analysis and gas pressure intensity test of FL-9 low-speed compressed-air wind tunnel;

The development and preliminary application of a pulse combustion wind tunnel with new running way;

By analyzing the development of hypersonic wind tunnels in the world,a detailed scheme is presented for Nanjing University of Aeronautics & Astronautics Hypersonic Wind Tunnel(NHW),and it is the indices and the requirements of NHW.

Especially within the recent ten years in China,the progress in pressure distribution measurements by using PSP technique on wing surface of airplane model in low speed and high speed wind tunnels,on vane surface of air-turbine in subsonic cascade wind tunnel,and on the guide vane of axial counter-rotating compressor is introduced in this review.

According to the dynamic state characters of the sand and dust particles in wind tunnels,an improved particles system has been constructed based on the tradition way.