Abstract: A test article described herein enables ground-based arc jet testing to investigate RF blackout mitigation using electrophilic gas injection upstream of an antenna. The article can be scaled up to actual flight vehicles, thereby allowing reentry vehicles to be in constant, or near constant, communication during atmospheric reentry. Plasma blackout mitigation is an enabling technology that is required to advance hypersonic flight. Example articles include an integral structure that supports a nozzle, piping for gas connected to the nozzle and an RF window. An ablator can be attached to the structure. The ablator can include a graphite ablator and an insulator. A flight vehicle can include an antenna and such an article.

Abstract: A test article described herein enables ground-based arc jet testing to investigate RF blackout mitigation using electrophilic gas injection upstream of an antenna. The article can be scaled up to actual flight vehicles, thereby allowing reentry vehicles to be in constant, or near constant, communication during atmospheric reentry. Plasma blackout mitigation is an enabling technology that is required to advance hypersonic flight. Example articles include an integral structure that supports a nozzle, piping for gas connected to the nozzle and an RF window. An ablator can be attached to the structure. The ablator can include a graphite ablator and an insulator. A flight vehicle can include an antenna and such an article.

Abstract: Disclosed are immobilized dimercapto succinate compounds (immobilized dithiol compounds), a method to synthesize these immobilized dithiol compounds, and a method of using the immobilized dithiol compounds to remove metals, such as lead, cadmium and mercury from an aqueous solution. Also disclosed are immobilized mono- and di-citrate compounds (immobilized citrate compounds), a method to synthesize these solid-supported compounds, and a method of using the immobilized citrate compounds to remove trivalent metals, such as iron and aluminum from an aqueous solution.

Abstract: A turbine engine component, such as a turbine blade, has an airfoil portion, a plurality of cooling passages within the airfoil portion with each of the cooling passages having an inlet for a cooling fluid. Each inlet has a flared bellmouth inlet portion. The turbine engine component may further have a dirt funnel at the tip of the airfoil portion, a platform with at least one beveled edge, and an undercut trailing edge slot.

Abstract: A turbine engine component, such as a turbine blade, has an airfoil portion, a plurality of cooling passages within the airfoil portion with each of the cooling passages having an inlet for a cooling fluid. Each inlet has a flared bellmouth inlet portion. The turbine engine component may further have a dirt funnel at the tip of the airfoil portion, a platform with at least one beveled edge, and an undercut trailing edge slot.