These spare parts will be assembled to create a nearly-complete Delta II, for exhibition in its 7420-10 configuration. The rocket will be displayed vertical at the Kennedy Space Center Visitors Complex, and may bear its popular "shark teeth" livery on its fairing, which was painted on past Delta II rockets for the GPS launches. The first stage of the Delta II was propelled by a Rocketdyne RS-27 main engine burning RP-1 and liquid oxygen. This stage was technically referred to as the "Extra-Extended Long Tank Thor", a derivative of the Thor ballistic missile as were all Delta rockets until the Delta IV. The RS-27 used on the 6000-series Delta II produced 915 kN, while the upgraded RS-27A used by the 7000-series produced 1,054 kN. The stage was 26 meters long and 2.4 meters wide, weighted over 100 t when fueled, and burned for 260 seconds. In addition, two LR101-NA-11 vernier engines provided guidance for the first stage. For additional thrust during launch, the Delta II used solid boosters. For the 6000-series, Delta II used Castor 4A boosters, while the 7000-series used Graphite-Epoxy Motors manufactured by ATK. The vehicle could be flown with three, four, or, most commonly, nine boosters. When three or four boosters were used, all ignited on the ground at launch, while models that used nine boosters would ignite six on the ground, then the remaining three in flight after the burnout and jettison of the first six. The second stage of Delta II was the Delta-K, powered by a restartable Aerojet AJ10-118K engine burning hypergolic Aerozine-50 and . These propellants are highly toxic and corrosive, and once loaded the launch had to occur within approximately 37 days or the stage would have to be refurbished or replaced. This stage also contained a combined inertial platform and guidance system that controlled all flight events. The Delta-K stage was 6 meters long and 2.4 meters wide, containing up to 6 t of propellant, and burned for up to 430 seconds. For low Earth orbit, Delta II was not equipped with a third stage. Payloads bound for higher energy orbits such as GTO or to reach Earth escape velocity for trans-Mars injection or other destinations beyond Earth used a solid propellant third stage. This stage was spin-stabilized and depended on the second stage for proper orientation prior to stage separation, but was sometimes equipped with a nutation control system to maintain proper spin axis.