Investigation of liquid fluorine and hydrazine-ammonia mixture in 100-pound-thrust rocket engine

Paul M. Ordin, Edward A. Rothenberg, William H. Rowe
Oct 1952

Specific impulse, characteristics velocity, thrust coefficient, and heat rejection of liquid fluorine and a fuel consisting of a hydrazine-ammonia mixture were determined for a range of fuel percentages (fuel to total propellant flow) in a 100-pound-thrust rocket engine designed for a combustion-chamber pressure of 300 pounds per square inch absolute. The fuel consisted of 59 percent hydrazine, 37 percent ammonia, and 4 percent water.

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