A simple prediction model of the thrust coefficient of linear aerospike nozzles was proposed. In the model, thrust coefficient efficiency of the momentum thrust of the cell nozzles and the base pressure, was empirically determined based on the experimental data. The average base pressure was determined to coincide the predicted thrust efficiency with the experimental efficiency at the design NPR of the spike nozzle. The case of a truncated-spike nozzle with the secondary injection was included in the mode. The case of a truncated-spike nozzle with the partial side-fence, in which the lower side-fences from the truncation point were cut off, was also evaluated. In all cases, the predicted values from this proposed model showed good agreement with the experimental data at all NPR conditions.
展开▼
