Propulsion Calculator

The formula for transonic flow is typically described using the Mach number, which represents the speed of an object relative to the speed of sound in the surrounding medium. Where: M = Mach number V = velocity of the object a = speed of sound in the medium

Incompressible flow is a fluid flow in which the density of the fluid remains constant throughout the flow field. In other words, the flow is such that changes in pressure and temperature do not significantly alter the density of the fluid. Where: ˙m˙ is the mass flow rate (constant) ρ is the density of the

A Mach cone, also known as a Mach shock wave or Mach angle, is a cone-shaped region of compressed air or gas that forms around an object moving through a fluid (such as air or water) at a speed greater than the speed of sound in that fluid. Where: θ is the angle of the

The Prandtl-Glauert transformation, also known as the compressibility correction, is used to correct the lift and drag coefficients calculated for an incompressible flow to account for the effects of compressibility at high speeds. It’s expressed as: ​ Where: CLα​ is the lift coefficient corrected for compressibility effects. CL0​ is the lift coefficient at a specific

The critical Mach number is the velocity at which the airflow over an object or airfoil reaches the speed of sound. It’s a significant parameter in aerodynamics because it marks the boundary between subsonic and supersonic flow regimes. Where: Mcr​ is the critical Mach number, γ is the specific heat ratio (ratio of specific heats),

The formula for calculating flap deflection depends on various factors such as the type of flap, the aircraft’s configuration, and aerodynamic considerations. This formula relates the change in lift coefficient (due to flap deflection) to the change in flap angle.

Lift augmentation refers to the increase in lift generated by an aircraft beyond its baseline or nominal lift characteristics. This increase in lift can be achieved through various means such as deploying flaps, slats, leading-edge devices, or other aerodynamic modifications. Where: ΔCL​ is the lift augmentation factor (dimensionless). S add-on​ is the added-on lifting surface

The stall angle formula typically refers to the angle of attack at which an airfoil stalls, causing a sudden decrease in lift. It depends on factors such as the airfoil shape and characteristics. One commonly used formula to estimate the stall angle is:  

Induced drag is a type of drag generated by the production of lift on a finite wing. When an aircraft generates lift, it creates vortices at the wingtips due to the pressure difference between the upper and lower surfaces of the wing. Where: Di​ = induced drag L = lift ρ = air density V

Pressure drag, also known as form drag or profile drag, is a component of drag force experienced by an object moving through a fluid (such as air or water) due to the pressure differential between the front and rear surfaces of the object. Where: Fd​ is the pressure drag force. ρ is the density of