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

Cylindrical, canted at about 30 degrees at one end for internal elliptical nozzle exit; plumbing at other end consisting of two parallel rods in V-arrangement, 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; holes drilled into flange at lower side for fitting onto spacecraft side. Overall, stainless steel, with brown phenolic nozzle protruding from nozzle flange. Small rectangular black and white metal manufacturer's plate mounted around top of cylinder, or thrust chamber. Red stripe around top of chamber cylinder, indicating this engine was not acceptable for flight.