Accession Number : AD0746618

Title :   Maximum Thrust Nozzles,

Corporate Author : BALLISTIC RESEARCH LABS ABERDEEN PROVING GROUND MD

Personal Author(s) : Conway,W. E. ; Celmins,A.

Report Date : MAY 1972

Pagination or Media Count : 28

Abstract : The report gives a correct formulation of the variational problem for the computation of maximum thrust nozzles. The relation between Rao's solution of the maximization problem and the correctly treated variational problem is clarified by demonstrating that Rao's family of characteristics is a special subset of the solutions of Euler's equations. It is shown further that other properly selected subsets as well as Rao's subset can be used to obtain the contour of a maximum thrust nozzle. Typical calculations of the thrust generated by maximum thrust nozzles and comparable conical nozzles show that properly dimensioned conical nozzles are adequate for most purposes Possible exceptions may be space rockets. (Author)

Descriptors :   (*CONICAL NOZZLES, THRUST), (*ROCKET NOZZLES, OPTIMIZATION), SUPERSONIC FLOW, NOZZLE GAS FLOW, COMPRESSIBLE FLOW, NOZZLE THROATS, NOZZLE AREA RATIO, NUMERICAL ANALYSIS

Subject Categories : Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE