Use of an approximate similarity principle for the thermal scaling of a full-scale thrust augmenting ejectorFull temperature ejector model simulations are expensive, and difficult to implement experimentally. If an approximate similarity principle could be established, properly chosen performance parameters should be similar for both hot and cold flow tests if the initial Mach number and total pressures of the flow field are held constant. Existing ejector data is used to explore the utility of one particular similarity principle; the Munk and Prim similarity principle for isentropic flows. Static performance test data for a full-scale thrust augmenting ejector are analyzed for primary flow temperatures up to 1560 R. At different primary temperatures, exit pressure contours are compared for similarity. A nondimensional flow paramenter is then used to eliminate primary nozzle temperature dependence and verify similarity between the hot and cold flow experiments.
Document ID
19920071547
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Barankiewicz, Wendy (NASA Lewis Research Center Cleveland, OH, United States)
Perusek, Gail P. (NASA Lewis Research Center Cleveland, OH, United States)
Ibrahim, Mounir (Cleveland State University OH, United States)