| Popis: |
The development of the new hypersonic impulse facility at the University of Michigan capable of generating aerothermal flow conditions representative of flight Mach numbers ranging between 4 and 11 is discussed. Three conditions were designed and run extensively for the purposes of validating and characterizing the generated flows. The conditions were chosen to span a range of accessible flow properties while maintaining relevance to the studies of supersonic combustion. The performance of the facility was assessed based on its ability to repeatedly and accurately generate flow conditions of interest. The temporal and spatial uniformity of the flow were determined using simultaneous pitotstatic pressure measurements, pressure measurements with a pitot rack, and schlieren imaging. Flow uniformity, useful test time, and core-flow sizes are established. A shot-to-shot statistical analysis of the resulting shock speeds reveal their variability to amount to a fraction of a percent, attributing to the ability of the facility to consistently generate the desired flow conditions. |
