Accession Number : AD0686161

Title :   THEORY OF ACCELERATED ROCKET NOZZLES,

Corporate Author : NEW YORK UNIV N Y DEPT OF AERONAUTICS AND ASTRONAUTICS

Personal Author(s) : Chiu,H. H.

Report Date : AUG 1968

Pagination or Media Count : 34

Abstract : The effect of the high acceleration of the rocket on the gas flow patterns in the nozzle and its performance characteristics are examined within one dimensional, quasi-steady formalism. The basic flow pattern in such a nozzle is predicted from the isentropic gas table through the use of 'Equivalence Principle' established in the analysis. The result of the analysis indicates that for a given stagnation condition in the combustion chamber, the velocity and the pressure of the gas at the exit of the accelerated nozzle is larger than that in the non-accelerated nozzle with the same cross sectional areas at the sonic throat, and also at the exit of two nozzles. The mass flow rate, the specific impulse and the total thrust are also found to be larger for the accelerated nozzles. The effect of the acceleration is found to be important for a highly accelerated nozzle with lower stagnation temperature. (Author)

Descriptors :   (*ROCKET NOZZLES, NOZZLE GAS FLOW), ONE DIMENSIONAL FLOW, ACCELERATION, NOZZLE AREA RATIO, NOZZLE THROATS, STAGNATION POINT, PERTURBATION THEORY, PARTIAL DIFFERENTIAL EQUATIONS, SPECIFIC IMPULSE, THRUST

Subject Categories : Fluid Mechanics
      Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE