Question: Project Wizard was to defend against threats from what missile with a liquid-propellant rocket engine, that was developed during WWII in Germany as a vengeance weapon?

Context articles: S1.5400
PGM-19 Jupiter
Walter HWK 109-507
Project Wizard
Liquid-propellant rocket
XLR50
V-2 rocket
XLR81
Rocketdyne F-1
RD-253

The S1.5400 (GRAU Index 11D33) was a Soviet single-nozzle liquid-propellant rocket engine burning liquid oxygen and kerosene in an oxidizer-rich staged combustion cycle, being the first rocket engine to use this cycle in the world.
 It was designed by V. M. Melnikov, an alumnus of Isaev, within Korolev's Bureau, for the Molniya fourth stage, the Block-L.
 It was also the first Soviet engine designed for start and restart in vacuum and had the highest "I" at the time of its deployment.
The PGM-19 Jupiter was the first nuclear tipped, medium-range ballistic missile (MRBM) of the United States Air Force (USAF).
 It was a liquid-propellant rocket using RP-1 fuel and LOX oxidizer, with a single Rocketdyne LR70-NA (model S-3D) rocket engine producing 667 kN of thrust.
 It was armed with the 1.1 megaton W49 nuclear warhead.
 The prime contractor was the Chrysler Corporation.
The HWK 109-507 was a liquid-propellant rocket engine developed by Germany during World War II.
 It was used to propel the Hs 293 anti-ship guided missile.
Project Wizard was a Cold War-era anti-ballistic missile system to defend against short and medium-range threats of the V-2 rocket type.
 It was contracted by the US Army Air Force in March 1946 with the University of Michigan's Aeronautical Research Center (MARC).
 A similar effort, Project Thumper, started at General Electric.
A liquid-propellant rocket or liquid rocket is a rocket engine that uses liquid propellants.
 Liquids are desirable because their reasonably high density allows the volume of the propellant tanks to be relatively low, and it is possible to use lightweight centrifugal turbopumps to pump the propellant from the tanks into the combustion chamber, which means that the propellants can be kept under low pressure.
 This permits the use of low-mass propellant tanks, resulting in a high mass ratio for the rocket.
The GE X-405 — U.S. Navy designation XLR50-GE-2 — was a pump-fed liquid-propellant rocket engine burning RP-1 and LOX in a gas generator cycle developed by General Electric.
 It was used to power the first stage of the Vanguard rockets on the Vanguard project.
 As was common to engines based on the V-2 experience, the turbine was driven by steam generated by catalytic decomposition of HO and the combustion chamber was regeneratively cooled.
 The engine was gimbaled to supply thrust vectoring.
 Also, the exhaust gases of the turbine were ducted to dual auxiliary nozzles that acted as verniers to enable roll control of the rocket.
The V-2 (German: "Vergeltungswaffe 2" , "Retribution Weapon 2"), technical name Aggregat 4 (A4), was the world's first long-range guided ballistic missile.
 The missile with a liquid-propellant rocket engine was developed during the Second World War in Germany as a "vengeance weapon", assigned to attack Allied cities as retaliation for the Allied bombings against German cities.
 The V-2 rocket also became the first artificial object to travel into outer space by crossing the Kármán line with the vertical launch of MW 18014 on 20 June 1944.
The Bell Aerosystems Company XLR81 (Model 8096) was an American liquid-propellant rocket engine, which was used on the Agena upper stage.
 It burned UDMH and RFNA fed by a turbopump in a fuel rich gas generator cycle.
 The turbopump had a single turbine with a gearbox to transmit power to the oxidizer and fuel pumps.
 The thrust chamber was all-aluminum, and regeneratively cooled by oxidizer flowing through gun-drilled passages in the combustion chamber and throat walls.
 The nozzle was a titanium radiatively cooled extension.
 The engine was mounted on an hydraulic actuated gimbal which enabled it thrust vectoring to control pitch and yaw.
 Engine thrust and mixture ratio were controlled by cavitating flow venturis on the gas generator flow circuit.
 Engine start was achieved by solid propellant start cartridge.
The F-1 is a gas-generator cycle rocket engine developed in the United States by Rocketdyne in the late 1950s and used in the Saturn V rocket in the 1960s and early 1970s.
 Five F-1 engines were used in the S-IC first stage of each Saturn V, which served as the main launch vehicle of the Apollo program.
 The F-1 remains the most powerful single combustion chamber liquid-propellant rocket engine ever developed.
The RD-253 (Russian: "Раке́тный дви́гатель 253" , "Rocket Engine 253") and its later variants, the RD-275 and RD-275M, are liquid-propellant rocket engines developed in the Soviet Union by Energomash.
 The engines are used on the first stage of the Proton launch vehicle and use an oxidizer-rich staged combustion cycle to power the turbopumps.
 The engine burns UDMH/NO, which are highly toxic but hypergolic and storable at room temperature, simplifying the design.