Question: When was lift off for the Apollo 11 Saturn V rocket?
About the article "Space Race", section "Apollo 11".

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Saturn V Dynamic Test Vehicle, designated SA-500D, is a prototype Saturn V rocket used by NASA to test the performance of the rocket when vibrated to simulate the shaking which subsequent rockets would experience during launch.
It was the first full-scale Saturn V completed by the Marshall Space Flight Center (MSFC).
Though SA-500D never flew, it was instrumental in the development of the Saturn V rocket which propelled the first men to the Moon as part of the Apollo program.
Built under the direction of Dr. Wernher von Braun, it served as the test vehicle for all of the Saturn support facilities at MSFC.SA-500D is the only Saturn V on display that was used for its intended purpose, and the only one to have been assembled prior to museum display.
It is on permanent display at the U.S. Space & Rocket Center, Huntsville, Alabama. 
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. 
Documentaries often use footage of a Saturn V launch, and one of the most used pieces shows the interstage between the first and second stages falling away.
This footage is frequently mistakenly attributed to the Apollo 11 mission, when it was actually filmed on the flights of Apollo 4 and Apollo 6.
The cameras filmed at high speeds causing an estimated 15 times slow-motion view of the sequence when seen in a documentary.
The camera capsules were jettisoned soon after the first stage separation, and, though at about 200,000 feet in altitude, were still below orbital velocity.
They then reentered the atmosphere and parachuted to the ocean, where they floated waiting for recovery.
Only one of the two S-II cameras on Apollo 6 was recovered; the other was lost due to a problem with its locator beacon.
Another launch shot often attributed to Apollo 11 and other launches was shot on this day: it shows a view of the rocket lifting up, positioned relatively close up and dead center.
The shot can be identified as Apollo 6 by examining the Apollo Service Module on the launch; Apollo 6 was the only Saturn V-launched Apollo craft with a white SM; all others were silver. 
The MLP was constructed for transporting and launching the Saturn V rocket for the Apollo program lunar landing missions of the 1960s and 1970s.
Each MLP originally had a single exhaust vent for the Saturn V's engines.
The MLPs also featured a Launch Umbilical Tower (LUT) with nine arms that permitted servicing of the vehicle on the launch pad, and swung away from it at launch.
For Skylab and Apollo-Soyuz, MLP No.
1 was modified with a so-called "milkstool" pedestal that allowed the shorter Saturn IB rocket to use the Saturn V tower and service arms, and Saturn V Ground Support Equipment (GSE) was removed or de-activated and Saturn IB GSE equipment was installed. 
 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.