Propulsion Calculator

A drag equation calculator is a tool or software program used to compute the drag force acting on an object moving through a fluid. The drag equation, which is typically used in these calculators, relates the drag force to various parameters such as the shape of the object, its velocity relative to the fluid, the […]

Viscous drag refers to the resistance experienced by an object moving through a fluid due to the frictional forces between the object’s surface and the fluid. Where: F is the viscous drag force Cd is the drag coefficient, a dimensionless quantity that depends on the shape of the object and the Reynolds number ρ is

 Drag force refers to the resistance encountered by the object due to the interaction between its surface and the fluid it is moving through. Where: Fd​ represents the drag force experienced by the object, ρ is the density of the fluid (e.g., air or water), v is the velocity of the object relative to the

The angle of attack is the angle between the chord line of an airfoil (such as a wing) and the relative wind. It’s crucial in aerodynamics because it affects lift and drag forces on an aircraft. In the context of aerodynamics, the “opposite” side refers to the difference in height between the wing’s leading edge

Failure analysis involves investigating the causes of failures in materials, products, or systems. While there isn’t a single formula for failure analysis, it typically involves a combination of techniques such as root cause analysis, fault tree analysis, and various engineering principles to identify the factors contributing to the failure.

Nozzle efficiency is the ratio of the specific heat at constant pressure to the specific heat at constant volume. The pressure ratio is the ratio of the outlet pressure to the inlet pressure. Where: Actual exit velocity is the velocity of the fluid exiting the nozzle. Ideal exit velocity is the theoretical maximum velocity the

The efficiency of rocket propulsion is often measured by the specific impulse (Isp), which is the ratio of thrust produced to the rate of fuel consumption. The formula for specific impulse (Isp) is: Where: F is the thrust produced by the rocket. ˙m˙ is the rate of fuel consumption (mass flow rate). g​ is the

The performance analysis of a nozzle typically involves parameters such as exit velocity, mass flow rate, and efficiency. One common formula used for analyzing nozzle performance is the ideal nozzle equation: Where: Ve​ is the exit velocity of the fluid from the nozzle. g is the acceleration due to gravity. ΔℎΔh is the pressure difference across

The shock-boundary layer interaction is a complex phenomenon in fluid dynamics, particularly in high-speed aerodynamics. There isn’t a single formula to describe it, as it depends on various factors such as flow conditions, geometry, and boundary layer characteristics. However, researchers often use empirical correlations, numerical simulations, or theoretical models to study and predict these interactions.

The boundary layer formula relates the thickness of the boundary layer to various factors such as the Reynolds number, velocity, and characteristic length of the flow. One common formula for the boundary layer thickness in laminar flow over a flat plate is given by: Where: δ is the boundary layer thickness x is the distance