Propulsion Calculator

The oxidizer mass fraction is a crucial parameter in rocket propulsion systems, determining the proportion of oxidizer to the total propellant mass. To comprehend its significance, consider its impact on rocket performance and efficiency. In this formula: Mass of Oxidizer refers to the mass of the oxidizing agent used in the propulsion system. Total Mass […]

A propellant density equation calculator is a tool or program that helps you calculate the density of a propellant based on its mass and volume. The formula used in the calculator is typically: Where: ρ is the density of the propellant in kilograms per cubic meter (kg/m³). m is the mass of the propellant in

The reaction mass flow rate equation defines the rate at which mass flows through a system during a chemical reaction. It quantifies the amount of reacting material passing through a given area per unit time. Where: m˙r​ is the reaction mass flow rate (in kg/s), ρ is the density of the reacting fluid (in kg/m³),

The efficiency of a gas generator cycle can be calculated using the specific impulse equation, which relates the efficiency to the specific impulse and the effective exhaust velocity. The specific impulse is defined as the thrust produced per unit weight flow rate of propellant consumed. It’s expressed as: where Ve​ is the effective exhaust velocity

Stagnation pressure, also known as total pressure or pitot pressure, is a thermodynamic property of a fluid flow. It represents the pressure that a fluid would possess if it were brought to rest isentropically (without any losses due to friction or turbulence) from its current velocity. Where: P is the static pressure of the fluid,

The formula for calculating the divergence angle of a nozzle depends on the specific type of nozzle being used. For a convergent-divergent (CD) nozzle, which is commonly used in rocket propulsion, the divergence angle can be calculated using the following formula: Where: θd​ is the divergence angle, Me​ is the exit Mach number of the

The power-to-weight ratio is a measure of an object’s or system’s power output relative to its mass. It quantifies the amount of power generated or used per unit of weight, often expressed in terms of watts per kilogram (W/kg).

The formula for leading-edge slats is typically based on aerodynamic principles and specific aircraft design requirements. It involves factors such as airfoil shape, wing geometry, desired lift characteristics, and operational considerations. Where: ΔCLmax​​ is the increase in maximum lift coefficient. k is a coefficient representing the effectiveness of the slat system. Sslat​ is the area

High-lift devices are aerodynamic mechanisms or surfaces installed on aircraft wings to enhance lift during takeoff and landing phases. These devices modify the wing’s geometry temporarily to increase the wing area, change its camber, or both, thereby allowing the aircraft to generate more lift at lower speeds. Where: The lift coefficient of the aircraft without

A laminar boundary layer is a thin region of fluid flow that develops adjacent to a solid surface, typically in the presence of low to moderate flow velocities. In this layer, fluid particles move smoothly and parallel to the surface, with minimal mixing between adjacent layers. Laminar boundary layers are characterized by orderly fluid motion