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An analysis method has been developed to aid in the design of the ammonia thermal control system of the Space Station. Although developed for a specific thermal control system, the method is applicable to other systems with a similar working principle. The method uses SINDA/FLUINT models with basic concepts in engineering and statistics and comprises the logical approach to organizing a large number of pertinent parameters to obtain an optimum yet robust design and to evaluate the degradation of system performance caused by variations in the pertinent parameters. The analysis is described in the iterative design/analysis of the thermal control system and consists of the sizing of the ammonia lines, flow control orifices, the best-estimate model, and the departure from the best estimate of flow distribution due to the uncertainty bands of the system components.

This paper describes a new application of Karman vortex shedding frequency as a velocity sensor in a motored internal combustion engine cylinder. The probe design, experimental setup and data reduction procedures are described. The quality of data obtained depends strongly on the relative frequency distribution of the free-stream turbulence and of the vortex shedding induced by the vortex generator. The instrument was evaluated on a CFR engine equipped with a shrouded intake valve. The results are presented in terms of the airswirl ratio at several selected crank angle degrees versus engine speed. The limitations of the device were also demonstrated in L-head engine tests.