The design, fabrication and calibration of a new thrust stand for conducting thrust and
aeroacoustic measurements concurrently in a fully anechoic chamber is discussed. The new thrust stand employs the scale-force measurement technique and is designed to accommodate multi-stream nozzles (core and bypass flow streams). Each stream has a dedicated helium air mixture system thereby permitting a multitude of test conditions. The methodology for designing the thrust stand is described and uses a notch type flexure which demonstrates high repeatability over extended thrust ranges. Calibration is performed with elevated pressure inside the plenum to characterize the effect of increased pressure on the flexure performance. A further qualification of the thrust measurement accuracy is conducted using a small arsenal of nozzles comprising method of characteristics contours. Surveys of the far-field pressure are then conducted during various operating points along the startup curve of a Mach 1.71 rectangular supersonic nozzle.