Question: What was the exact time and date of lift off for the Saturn V rocket?
About the article "Space Race", section "Apollo 11".

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The Saturn family of American rocket boosters was developed by a team of mostly German rocket scientists led by Wernher von Braun to launch heavy payloads to Earth orbit and beyond.
Originally proposed as a military satellite launcher, they were adopted as the launch vehicles for the Apollo moon program.
Three versions were flown, the Saturn I, Saturn IB and the Saturn V. President John F. Kennedy identified the Saturn I SA-5 launch as being the point where US lift capability would surpass the Soviets, after having been behind since Sputnik.
This was last mentioned by him in a speech he gave at Brooks AFB in San Antonio on the day before he was assassinated.
To date, the Saturn V is the only launch vehicle to transport human beings beyond Low Earth Orbit.
A total of 24 humans were flown to the Moon in the four-years spanning December 1968 through December 1972. 
 Saturn-Shuttle   Saturn A-1, Saturn A-2, Saturn B-1  Saturn INT-18, a conceptual study in 1966 to build a rocket utilizing various Saturn V-components.
Numerous version were studied, with payload capacity between 21,300 and 66,590 kg to LEO (two heaviest variant had payload capacities of 51,700 kg and 66,400-66,590 kg to LEO.)
Saturn INT-20, a proposed launcher in the 1960s–1970s using the Saturn V-components.
Three variants were studied with the heaviest (the five-engine variant) having payload capacity of 60,500 kg to LEO, and the second heaviest (the four-engine variant) having payload capacity of 60,000 kg to LEO.
Saturn INT-21, described in a study of the 1970s to develop a smaller launcher based on Saturn V. It was expected to be composed of Boeing S-IC and modified North American S-II with payload capacity of 75,000 kg to LEO.
Also heavier variants with payload to LEO 84,000 kg, 89,000 kg, 101,000 kg, 112,000 kg and 116,000 kg were studied (the heavier variants had successively more engines).
Saturn MLV-V-1, a NASA study of an improved Saturn V rocket in 1965.
Payload to LEO 137,250 kg.
Saturn MLV-V-1A, a NASA study of an improved Saturn V rocket in 1965.
Payload to LEO 145,000 kg.
Saturn MLV-V-2, a NASA study to develop the Saturn V rocket in 1965.
Payload to LEO 137,250 kg   Saturn MLV-V-3, a NASA study in 1965 to improve the Saturn V. Payload to LEO 160,400 kg   Saturn MLV-V-4(S), rocket NASA studied in 1965.
A developed version of Saturn V. Payload 118,000 kg to LEO.
Saturn MLV-V-4(S)-A, a development of the Saturn V studied by NASA in 1965.
Payload to LEO 160,880 kg.
Saturn MLV-V-4(S)-B, a rocket studied by Boeing in 1967.
Was based on Saturn V. Payload to LEO 171,990 kg.
Saturn V 2, a 2-stage version of Saturn V. Used to launch Skylab.
Payload to LEO 75,000 kg.
Saturn V/4-260, a rocket studied by Boeing in 1967-1968.
Used Saturn V-components.
Payload to LEO 362,700 kg.
Saturn V-23(L), a Boeing study of a Saturn V-based rocket in 1967.
Payload to LEO 262,670 kg.
Saturn V-24(L), a Boeing study of a Saturn V-based rocket in 1967.
Payload to LEO 435,300 kg.
Saturn V-25(S)B, another Boeing study of a Saturn V-based rocket in 1967.
Payload to LEO 223,500 kg.
Saturn V-25(S)U, a Boeing study of a Saturn V-based rocket in 1968.
Would have been used to launch the NERVA nuclear rocket to orbit for Mars-expedition.
Payload to LEO 248,663 kg.
Saturn V-3B, a Boeing-studied variation of a Saturn MLV-V-3-study.
Studied in 1967.
Rocket was based in the Saturn V-rocket.
Payload capacity 166,600 kg to LEO.
Saturn V-4X(U), a Boeing-study in 1968 extending the Saturn V-25(S)-study.
Payload to LEO 527,600 kg.
Saturn V-A, a NASA-study in 1968 essentially identical to Saturn INT-20.
Payload to LEO 60,000 kg.
Saturn V-C, a NASA-study in 1968 extending the Saturn V-A and Saturn INT-20-studies.
Payload to LEO 81,600 kg.
Saturn V-Centaur, another NASA-study in 1968 extending the Saturn V-A and Saturn INT-20-studies.
Payload to LEO 118,000 kg.
Saturn V-D, a NASA-study of 1968 extending the Boeing study of 1967 to develop a Saturn V-based rocket.
Payload to LEO 326,500 kg.
Saturn V-ELV, a NASA study of 1966 to develop Saturn V-based rocket.
Payload to LEO 200,000 kg.
Saturn C-2, a launcher first studied in USA 1959-1961.
Design proposal cancelled in 1961 in favor Saturn C-3.
Saturn C-3, a launcher first studied in USA 1959-1962.
Final design revision became Saturn C-3B.
Saturn C-3B, a launcher studied in the USA in 1961.
Cancelled after the Saturn C-5 was selected for Apollo program(Saturn C-5-rocket later evolved into Saturn V).
Would have had the payload capacity of 78,000 kg to LEO.
Saturn C-3BN, a launcher studied in the USA in 1961.
Cancelled after the Saturn C-5 was selected for Apollo program; the Saturn V-rocket was based in the Saturn C-5.
Otherwise similar to Saturn C-3B, but would have utilized a nuclear upper stage.
Payload capacity of 94,000 kg to LEO.
Saturn C-4, an American launch vehicle studied for the lunar orbit rendezvous-method of lunar exploration.
Lost competition for the launcher of Apollo program to Saturn C-5 (Saturn C-5 was modified slightly during the 1960s to produce the Saturn V-rocket) because Saturn C-5 had reserve capacity that the Moon mission designers wanted.
Payload to LEO 99,000 kg.
Saturn C-4B, the last variant of Saturn C-4 before Saturn C-5 was chosen for the Moon landing in 1961 (Saturn C-5 was modified slightly during the 1960s to produce the Saturn V-rocket) and the development of other Saturn C-series rockets was halted.
Payload 95,000 kg to LEO.
Saturn C-5, the rocket chosen for Apollo program in 1961.
Saturn C-5's development was continued after it was chosen to be the American Moon rocket, and the result was Saturn V. The difference between Saturn C-5 and Saturn V (albeit small) is that the upper stages of Saturn V were enlarged in relation to the C-5.
The Saturn C-5-configuration of 1961 had payload capacity to LEO 120,000 kg.
Saturn C-5N, was a conceptual version of the Saturn V launch vehicle which would have had a nuclear third stage.
Payload to LEO 155,000 kg.
Saturn C-8, the largest of Saturn-variants to be considered.
Was intended for direct landing method of lunar exploration, like the Nova's.
Was abandoned after the Saturn C-5 was selected for Apollo (turn C-5 developed into the Saturn V).
Payload to LEO 210 ton.
Nova, a group of heavier-than-Saturn V launch vehicles studied by many American aerospace companies and NASA.
Some Nova-rockets (most notably Nova C-8, Nova 8L) were intended for direct landing method of lunar exploration like the Saturn C-8, and these rocket-designs were cancelled (like the Saturn C-8) after Saturn V was chosen for the Apollo program.
These rockets had payload capacity between 24-75 tons to translunar injection orbit TLI (Saturn V had payload capacity of 45 tons to TLI).
Other Nova-rockets were also intended for Mars missions in the 1960s-1970s.
The Mars-mission Nova-rockets had intended payload to LEO 301 ton - 455 ton.  
One of the most notable recipients was Wernher von Braun, who developed the V-2 rocket, and later designed the Saturn V rocket for the U.S. space program.
Also, Eberhard Heder and Otto Günsche. 
Two members of the Saturn family of rockets, the Saturn I and IB, were derived from the Redstone.
They used Redstone and Jupiter propellant tanks clustered together with eight Jupiter engines to form the first stage of the rockets.
First developed by the ABMA, the Saturn rocket was adopted by NASA for its Apollo program.
America's first heavy-lift launch vehicles, the first of these was launched in 1961. 
The Saturn Launch Vehicle Digital Computer (LVDC) was a computer that provided the autopilot for the Saturn V rocket from launch to Earth orbit insertion.
It was one of the major components of the Instrument Unit, fitted to the S-IVB stage of the Saturn V and Saturn IB rockets.
The LVDC also supported pre- and post-launch checkout of the Saturn hardware.