Aerodynamics Calculator

The stream function (ψ) is a mathematical function used to describe the flow of an incompressible fluid in two-dimensional flow scenarios. For a combined flow, the stream function represents the superposition of two or more individual flows. The combined flow can be achieved by adding or subtracting the stream functions of the individual flows.  The […]

The surface pressure coefficient (Cp​) is a dimensionless quantity used in fluid dynamics, especially in aerodynamics, to describe the pressure distribution over a body’s surface exposed to a fluid flow. It is commonly used to analyze and understand the aerodynamic forces acting on objects such as airfoils, wings, and other streamlined or bluff bodies. This

In aerodynamics, the flow around a cylinder can be described using potential flow theory. The flow has two components: the uniform flow component (V∞​) and the vortex flow component (Vθ​) due to circulation  (represented by Γ) around the cylinder.  Vr​ is the radial component of velocity Vθ​ is the tangential component of velocity V∞​ is

In aerodynamics, uniform flow refers to a type of ideal flow pattern where the fluid velocity remains constant across a large region. In the case of two-dimensional flow (flow that occurs within a plane). The stream function (ψ) is a mathematical function used to describe the flow of an incompressible fluid (such as air) in

Thermal conductivity (k) is a material property that measures how well a material conducts heat. It quantifies the ability of a substance to transfer thermal energy through conduction. In other words, it describes how easily heat flows through a material when there is a temperature gradient.  k is the thermal conductivity μ is the molecular

The lift slope (a) of the elliptical wing is related to the lift slope (a0) of the individual airfoil section from which the wing is constructed and the aspect ratio (AR) of the wing. The lift slope (a) for the entire wing is derived from the lift slope (a0) of the airfoil section but takes

Induced drag coefficient (CDi) is a dimensionless aerodynamic parameter that quantifies the portion of drag generated by the production of lift on a wing or an airfoil. When an aircraft generates lift to stay airborne, it also creates a certain amount of drag as a consequence. This type of drag is known as induced drag.

The coefficient of lift (CL) for a symmetric airfoil is a dimensionless parameter used in aerodynamics to quantify the lift generated by the airfoil when it is placed in a flow of air. For a symmetric airfoil, the upper and lower surfaces have the same shape, resulting in zero camber (i.e., the mean camber line

Stagnation points refer to specific locations in the flow field where the velocity of the fluid becomes zero, resulting in stagnation or zero velocity. For the flow over a cylinder, there are two primary types of stagnation points: the forward stagnation point and the rear stagnation point.  R is the radial coordinate of the stagnation

The radial velocity for a three-dimensional point source represents the velocity of the fluid flow at any given distance (r) from the point source. The point source is a theoretical concept used in potential flow theory to model fluid flow emanating from a single point or converging towards it. The radial velocity describes how the