THEORY OF ACCELERATED ROCKET NOZZLES,
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1968
- Accession Number
- AD0686161
Entities
People
- H. H. Chiu
Organizations
- New York University