Studies made at Rocket Propulsion Establishment of Ministry of Aviation to determine relationship between specific weight and thrust of liquid bi-propellant rocket engine; it is concluded that minimum specific weight is achieved at thrust level near 50,000 lb; difference in specific weight between engines of 200,000 and 50,000 lb thrust is only about 10% and this is shown to be equivalent to only 1% in propellant specific impulse.
Optimum size of rocket engine
Roy Aeronautical Soc -- J
Royal Aeronautical Society -- Journal ; 64 , n 600
1960
26 pages
Aufsatz (Zeitschrift)
Englisch
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