In the present study, an analytical model based on convective heat feedback is developed for the estimation of the solid fuel surface regression rate of hybrid rocket engines with head-end swirling-flow oxidizer injection. The convective heat transfer between the axial core flow and the burning fuel surface, coupled with the convective heat feedback between the effective tangential flow and the burning fuel surface, is the means by which the fuel regression rate is presumed to be increased by swirl, above that due to the axial mass flux. The representation of the effective boundary layers used in this study includes the influence of transpiration, effective hydraulic diameters (for flows in the axial and tangential direction), and fuel surface roughness. From the literature, a variety of propellant combinations, engine sizes, and flow swirl numbers are evaluated for engines having circular-port fuel grains, with sample model results provided. The predicted fuel regression rates for the most part compare quite well with the corresponding experimental data.
Regression Rate Estimation for Swirling-Flow Hybrid Rocket Engines
Journal of Propulsion and Power ; 32 , 1 ; 18-22
2015-09-15
5 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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