Rocket Engine, Liquid Fuel, Gemini Reentry Control System (RCS)

Cylindrical, canted at about 30 degrees at one end for internal nozzle exit; plumbing at other end consisting of two parallel vertical rods serving as propellant inlet lines, and other, smaller diameter pipes projecting from their sides with downward, goose neck ends. Canted nozzle end with matching angled mounting flange around opening; six holes drilled into flange at lower side for fitting onto spacecraft side; two yellow plastic protective caps over two small pipes and two black plastic wrappings over ends of two other small pipes; with mounting bracket. Overall, stainless steel, with brown phenolic nozzle protruding from nozzle flange; lacks usual nozzle protective cover. Small rectangular black and white metal manufacturer's plate mounted around top of cylinder, or thrust chamber. Two red stripes painted around top of cylinder or thrust chamber, and adajacent lettering, also in red, "Not Acceptable for Flight." Some traces of adhesive tape marks around nozzle, but unfired.