Analytical Investigation of Multinozzle Plume Flow Fields - Flow Structure and Computation.

摘要

Progress on the research effort is summarized. Major achievements include (a) the qualitative understanding of the complex shock structure impingement of two underexpanded rocket plumes and (b) the development of three dimensional computational techniques. A three dimensional isentropic inviscid supersonic computer code is operational and the core flow field of rectangular nozzles has been computed. Advanced techniques built around floating discrete discontinuity surfaces and singularity cells are being incorporated into this program for the computation of the impingement of two rectangular plumes.