Microchannel-Cooled Structure for Hypersonic Engine Inlets

A study will be conducted to develop actively-cooled structural concepts for high heat transfer engine inlet regions of scramjet engines. The program is directed toward the HyTech missile system and employs laminated foil microchannel cooling technology. The program will consist of four basic tasks: (1) definition of design requirements; (2) design trade studies to develop the optimum size, weight, and performance characteristics of the cooled structure; (3) fabrication and laboratory testing of an instrumented prototype cooled model; and (4) planning for a follow-on test program to validate the performance of the prototype design and the accuracy of the analytical design methods. The resultant cooled structure can be used as an alternative, or back up, concept to the passive structures under current development for the HyTech program, and can also be utilized as a constant shape, instrumented model holder for high heat flux testing of passive material panels.