Proposal for steadying flow from rocket nozzle on Space Shuttle main engine could be applied to other large-area-ratio contoured nozzles. Oscillations and pulsations in boundary-layer flow would be reduced by flaring nozzle exit. Transient side loads on nozzle would be suppressed. Large pressure gradients and eddies that can lead to fluctuations are suppressed. Exact radius of curvature of corner would depend on shear-layer thickness.
Nozzle Modification Suppresses Flow Transients
NASA Tech Briefs ; 6 , 1
1982-09-01
Sonstige
Keine Angabe
Englisch
Transients in Homogeneous Granular Pipe Flow
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