Article ID Journal Published Year Pages File Type
1715025 Acta Astronautica 2013 11 Pages PDF
Abstract
► A code for hybrid rocket unsteady operation and transit fuel regression is developed. ► Calculated thrust and chamber wall profile are in good agreement with test data. ► New coefficients for regression rate equation are derived. ► Regression rate is function of chamber diameter leading to analysis of scale effect.
Keywords
Related Topics
Physical Sciences and Engineering Engineering Aerospace Engineering
Preview
Combustion performance and scale effect from N2O/HTPB hybrid rocket motor simulations
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