<page_title> PGM-19 Jupiter </page_title> <section_title> Specifications (Juno II launch vehicle) </section_title> <table> <cell> Thrust <col_header> Parameter </col_header> </cell> <cell> 667 kN <col_header> First stage </col_header> </cell> <cell> Engine: <col_header> Parameter </col_header> </cell> <cell> Rocketdyne S-3D <col_header> First stage </col_header> </cell> <cell> Propellant <col_header> Parameter </col_header> </cell> <cell> LOX/RP-1 <col_header> First stage </col_header> </cell> </table>
PGM-19 Jupiter was a propellant using RP-1 fuel and LOX, with a Rocketdyne (model S-3D) engine producing 667 kN of thrust.