A-4 Rocket

Since the specific heat raho of the combushon gas, y, lies between 1.2 and 1.4, the ratio of the discharge coefficients, Cd, j/Cd,>> is 0-80 for y = 1.2 and 0.78 for y = 1.4. This result indicates that the mass flow rate from the port exit is approximately 20 % lower than that from the isentropic nozzle exit used for a convenhonal rocket motor when the head-end pressure is equal to the chamber pressure in the rocket motor.[5]... 

Schapery, R. A., Solid Rocket Structural Integrity Abstr. Ill (4) (Oct. 

Visol-6, according to Refs 2 4, was a Ger trade name for vinylethyl ether. It was used during WWII as a liq rocket propelling fuel in guided missiles such as the Enzian E-4, Rhein-tochter R-3 and Wasserfall. Absolute nitric acid was used as the oxygen carrier... 

Bipropellant. A rocket proplnt consisting of two unmixed chemicals(usually liquid) fed into the combustion chamber separately. One of the chemicals is a fuel(such as alcohol, aniline, hydrazine, etc), while the other is an oxidizeif such as liq O, nitric acid, hydrogen peroxide or nitrogen tetr-oxide). The energy released on combustion of fuel operates a propulsive rocket unit Refs l)warren( 1958), 13-14 2)Rocket Encycl (1959), 43-4... 

Princeton Univ Press, Princeton, NJ(1956),pp 470-513(70 refs) 24)C.Hugget, "Combustion of Solid Propellants , in the above book by Lewis et al,pp 514-74(98 refs) 25)F.A.Warren, "Rocket Propellants , Reinhold, NY(1958), 88-107 l37-40(Burning and burning rate of rocket propellants) 26)J.Taylor, "Solid Propellant and Exothermic Compositions , Interscience, NY(1959), 100-4(Burning rate of rocket proplnts) 27)J. 

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