A rocket engine is provided with a propellant valve controlling the output of a propellant tank. The valve is configured to induce a vortex in the propellant as it passes the propellant valve. Plural rocket engines may be supplied by a single valve, the valve inducing a vortex in the propellant which is then supplied to plural propellant lines configured to enhance the vortex induced by the valve.

A valve includes a generally cylindrical housing including first and second end portions that are offset from each other along a longitudinal axis of the generally cylindrical housing. First and second inlet ports are arranged on one of said first or second end portions, and at least one outlet port is arranged on one of said first or second end portions. A disk is disposed in the generally cylindrical housing and is configured to independently control both mixing and flow rate of fluid flowing into at least one of the first and second inlet ports.