Method for predicting nozzle performance of microthrust rockets is discussed. Method is numerical and uses simplified computer program on IBM 360/65 computer. Analysis is based on slender channel equations with slip boundary conditions at walls. Implicit finite difference scheme is used to calculate pressure and velocity profiles along channel.
Final report on a study of low-density nozzle flows, with application to microthrust rockets
01.12.1972
Sonstige
Keine Angabe
Englisch
Electrothermal microthrust systems.
NTRS | 1967
|Electrothermal microthrust systems
NTRS | 1967
|Electrothermal Microthrust Systems
NTIS | 1967
|Electrothermal microthrust systems
AIAA | 1967
|