Propulsion System Design Calculation Excel Template

Propulsion system design involves balancing thrust, specific impulse, mass flow rate, efficiency, and structural constraints to meet mission objectives such as delta-v, payload capacity, and operational lifetime. The Excel template codifies first-principles physics—including the ideal rocket equation, Brayton and Carnot cycle efficiencies, nozzle isentropic flow relations, and thrust-to-weight optimization—into modular, interlinked worksheets. Each worksheet often corresponds to a subsystem (e.g., combustion chamber, nozzle, turbomachinery, or battery-powered motor), with built-in error checking, unit consistency (SI and Imperial toggle), and parametric sliders for rapid scenario exploration. Advanced versions incorporate Monte Carlo uncertainty propagation, regression-based empirical correlations (e.g., for combustion instability or nozzle erosion), and export interfaces for coupling with CAD or trajectory simulation tools. This resource bridges theoretical education and practical engineering, serving both academic instruction—where students learn cause-effect relationships through editable formulas—and industry prototyping—where preliminary feasibility assessments reduce reliance on costly CFD or test campaigns.