AbstractAn optimization approach, based on computational fluid dynamics methodology, is investigated for the performance prediction and optimization of liquid rocket engine nozzle. The CFD code employs implicit Lower-Upper decomposition (LU) scheme for solving the two-dimensional axisymmetric Navier–Stokes (NS) equations and species transport equations in an efficient manner. The validity of the code is demonstrated by comparing the numerical calculations with both the experimental data and previous calculations. Then the code, called by three optimization algorithms (i.e. successive quadratic programming method, genetic algorithm and interdigitation strategy) respectively, is used to design axisymmetric optimum-thrust nozzle. Results show that improvement on nozzle thrust can be obtained over that of the baseline case.
Performance prediction and optimization for liquid rocket engine nozzle
Aerospace Science and Technology ; 11 , 2-3 ; 155-162
2006-07-13
8 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Performance prediction and optimization for liquid rocket engine nozzle
Online Contents | 2007
|Theoretical liquid rocket engine nozzle flow fields
AIAA | 1992
|British Library Conference Proceedings | 2004
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