A low turbulence level cascade wind tunnel with a 36 m/s maximum velocity in a cross-section of 18" x 18" is the major equipment of this laboratory. This facility has been extensively used to study problems such as: The effect of free stream turbulence on flat plate, airfoil and cascade wakes; Turbulence measurements in endwall corner regions; Combined effects of roughness and free stream turbulence on skin friction. The laboratory also contains a two-stage axial flow compressor facility which has been used to study problems of turbulence at rotor tip blades and in rotating wakes as well as inlet distortion effects on performance.