Experimental investigation of a newly designed supersonic wind tunnel

Abstract

The §ow characteristics of the tandem nozzle supersonic wind tunnel at the Institute of Fluid Mechanics, Technische Universitat Braunschweig, are investigated. Conventional measurement techniques were utilized. The §ow development is examined by pressure sensors installed at various streamwise positions. The temperature is measured in the storage tube and the settling chamber. The in §uence of §ow treatment in the settling chamber on the §ow quality is also studied. The §ow quality of test section is evaluated by a 6-probe Pitot rake. The pressure §uctua-tions in the test section are studied by a sharp cone model. Eventually, good agreement between the measurements and numerical simulation of the tunnel design is achieved.

Interaction of Wake and Propulsive Jet Flow of a Generic Space Launcher

“…The flow conditions in the test section are constant for approximately 50 ms and the maximum achievable unit Reynolds number is Re = 35.3 • 10 6 1/m. The original design of the wind tunnel is described in [11] and the supersonic configuration is discussed in [32,33].…”

Numerical Prediction and Experimental Verification of Flow Field in Hypersonic Wind Tunnel

“…Carandente established the numerical simulation model of the SPES facility to investigate the possibility to simulate the entry conditions into Titan's atmosphere [12]. Wu built the wind tunnel in the Institute of Fluid Mechanics, Technical University Braunschweig, and established a numerical model to obtain the flow field inside the wind tunnel [13,14]. Although studies of flow field in the wind tunnel can be back to 1950s, the mechanism is not fully understood yet [15,16].…”