Abstract: A shapeable inlet manifold for a hypersonic scramjet includes an inlet lower cowling; a mount surface; and an inlet stream surface movably coupled to the mount surface, wherein the inlet lower cowling and the inlet stream surface define an opening of the shapeable inlet manifold allowing fluid flow therethrough. The inlet stream surface has first and second dispositions relative to the lower cowling defining first and second shapes of the opening, thereby providing respective first and second flow characteristics through the inlet manifold during flight.

Abstract: A method of thermally protecting a leading edge of a hypersonic system includes saturating an annular primary wick in contact with an evaporator and having a first pore size with a phase change material by means of an annularly-inward secondary wick having a second pore size and being coupled to a liquid line, the second pore size being larger than the first, where a first end of the secondary wick extends into a reservoir and a second end of the secondary wick extends into the evaporator, the second end of the secondary wick having a terminal end. The method includes terminating the liquid line inside of the evaporator, transferring thermal energy from the leading edge into the phase change material, raising the temperature of the phase change material to a phase-change temperature, changing phase of the phase change material, and carrying away heat from the leading edge.

Abstract: A method of designing a hypersonic vehicle includes selecting a shock shape; tracing a leading edge along the shock shape; selecting a base plane defining endpoints of the leading edge and rearwardly displaced from a front of the leading edge; and tracing stream surfaces back from the leading edge along the shock to the base plane in order to define an upper surface and a lower surface, wherein the upper and lower surfaces and base plane enclose a volume representing internal volume of the hypersonic vehicle. The lower stream surface is controllably morphable.

Abstract: A shapeable inlet manifold for a hypersonic scramjet includes an inlet lower cowling; a mount surface; and an inlet stream surface movably coupled to the mount surface, wherein the inlet lower cowling and the inlet stream surface define an opening of the shapeable inlet manifold allowing fluid flow therethrough. The inlet stream surface has first and second dispositions relative to the lower cowling defining first and second shapes of the opening, thereby providing respective first and second flow characteristics through the inlet manifold during flight.

Abstract: A method of designing a hypersonic vehicle includes selecting a shock shape; tracing a leading edge along the shock shape; selecting a base plane defining endpoints of the leading edge and rearwardly displaced from a front of the leading edge; and tracing stream surfaces back from the leading edge along the shock to the base plane in order to define an upper surface and a lower surface, wherein the upper and lower surfaces and base plane enclose a volume representing internal volume of the hypersonic vehicle. The lower stream surface is controllably morphable.

Abstract: A method for automatically determining performance characteristics of a scramjet engine uses a 1-dimensional approximation that includes obtaining a first set of environmental conditions defining freestream conditions; generating inlet outflow conditions by evaluating a change in flow from the freestream conditions across the inlet; generating isolator outflow conditions by modeling change in flow from the inlet outflow conditions across the isolator; generating combustor outflow conditions by modeling change in flow from the isolator outflow conditions across the combustor; and generating nozzle outflow conditions by modeling change in flow from combustor outflow conditions across the nozzle.