Drag Force Calculator

About this calculator

This calculator computes aerodynamic drag force using the standard drag equation: F = ½ρv²CₔA, where ρ is fluid density, v is velocity, Cₔ is the dimensionless drag coefficient, and A is the frontal (reference) area facing the flow. The drag coefficient captures how streamlined an object's shape is — a sphere might have Cₔ around 0.47, while a streamlined airfoil can be under 0.05.

Aerospace and automotive engineers use this formula to size wings, estimate fuel efficiency, and predict terminal velocity for skydivers and falling objects. Enter the fluid density (typically air at sea level, 1.225 kg/m³), velocity, drag coefficient, and frontal area to get the resulting force in newtons.