For the characteristic velocity of a rocket engine which is not available as an explicit function of mixture ratio and combustion chamber pressure an approximate method is presented. In applying to the equilibration of experimentally obtained values of the characteristic velocity efficiency its representation as a function of both variables is made possible. Based on a series of runs with a high-energy experimental rocket engine, the utility of this method is verified. (Author)
Beitrag Zur Darstellung von Kennfeldern Chemischer Raketentriebwerke. (Contribution Toward the Representation of the Characteristics of a Chemical Rocket Engine)
1969
8 pages
Report
Keine Angabe
Englisch