Development of an Experimental Data Base to Validate Compressor-Face Boundary Conditions Used in Unsteady Inlet Flow Computations
Dr. MiNos SajbenDr. Donald D. FreundDepartment of Aerospace Engineering and Engineering MechanicsUniversity of CincinnatiFinal Technical ReportResearch Grant Award fromNational Aeronautics and Space AdministrationNASA Lewis Research CenterPenod of Performance: January 1, 1997 to December 31, 1997May 15, 1998
Unsteady Inlet/Compressor Interaction Experiment to Support the Modeling of Compressor-Face Boundary Conditions
Atmospheric disturbances affecting high-speed, air-breathing propulsion systems may induce rapid flow transients. Such processes usually involve strong interactions between the inlet and the engine, and may lead to undesirable or even unacceptable consequences (e.g. inlet unstart, compressor stall or surge). Their reliable prediction requires, in principle, the simultaneous computation of the flow in both the inlet and the compressor. Such computations, while may be feasible in some simplified form [1,2], are too complex to fit into the cost and time constraint of industrial design processes. Current engineering practice is to perform computations for the two components separately, relying on the compressor face boundary conditions (CFBC’s) to represent the engine for the inlet flow predictions, or the inlet for engine calculations.
Laminar heat or mass transfer in rectangular channels and in cylindrical tubes for fully developed flow: comparison of solutions obtained for various boundary conditions
Abstract A comparison is made of results obtained with various boundary conditions at the wall of the channels. By comparing blood Sherwood numbers for finite wall resistance with those for constant concentration boundary condition only a small variation is found for various points along the blood channel.