Body impingement situations, where plumes from one spacecraft impinge on another, were examined in relation to Columbus and Hermes. Plume models relative to axisymmetrical configurations were reviewed. Model INTERJET was applied to the MBB 400 N bipropellant engine, yielding results consistent with those of another model. The choice of the data to be introduced as input when calculating a real thruster was examined. A computer code SCARFN was developed, based on a model for calculating the performance of a scarfed nozzle, together with a model for the description of plumes from scarfed nozzles. This model was applied to the same thruster, assumed to be equipped with a scarfed nozzle. A simplified model for nozzle performance was examined and the conditions for its validity were pointed out. An experimental program tested the validity of the models. Density and Pitot pressure distributions in plumes issued from three nozzles (one axisymmetrical) were obtained. Discrepancies between experimental and predicted flowfields are observed, essentially in the case of the nozzles with a high exit Mach number. Potential explanations lie in the experimental procedure and in the model.
Rocket Exhaust Plumes Issued from Axisymmetrical and Scarfed Nozzles, Executive Summary
1988
51 pages
Report
No indication
English
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