Aerodynamics Calculator

In aerodynamics, the Circulation at the origin (Γo) is a fundamental parameter used to describe the flow field around an elliptical wing. It quantifies the strength of the circulation around the wing and is a crucial concept in potential flow theory. The Circulation at the origin (Γo) is associated with the lift generated by the […]

The heat transfer coefficient (CH) is a measure of how effectively heat is transferred between a solid surface and a fluid (liquid or gas) flowing over or around it. It is a critical parameter in heat transfer analysis and plays a crucial role in various engineering applications, such as designing heat exchangers, cooling systems, and

The lift slope (a) for a finite wing is a parameter used to describe the change in lift coefficient (CL) with respect to the geometric angle of attack (α) of the wing. It is a measure of the wing’s effectiveness in generating lift as the angle of attack is varied. The lift slope represents the

The effective angle of attack (αeff) is a concept used in aerodynamics to describe the net angle at which the relative airflow interacts with an airfoil or wing. It accounts for both the geometric angle of attack (α) and the induced angle of attack (αi). αeff is the effective angle of attack. α is the

Induced drag is one of the two main components of drag experienced by an aircraft during steady, level flight. The other component is parasite drag. Induced drag is specifically related to the lift generated by the aircraft’s wings.  Di is the induced drag. e is the span efficiency factor, representing the effectiveness of the wing

The velocity potential (ϕ) is a scalar function used to describe the flow of an irrotational, incompressible fluid. It is a fundamental concept in potential flow theory, which simplifies fluid flow analysis by assuming the absence of vorticity (no swirling or rotational motion) and incompressibility, and neglects viscosity effects.  ϕ is the velocity potential due

A “point source” specifically represents a location in the flow field where fluid is injected or removed at a constant rate from a single point. A point source can be visualized as an imaginary or real location where fluid is introduced into the flow or extracted from it uniformly in all directions.  ϕ is the

The coefficient of lift (CL) is a dimensionless quantity used in aerodynamics to characterize the amount of lift generated by an aerodynamic object, such as an airfoil or wing, relative to the fluid flow around it.  CL: Lift coefficient e: Oswald’s efficiency factor AR: Aspect ratio CD,o: zero lift drag coefficient 

The zero-lift drag coefficient (CD,o) is a fundamental aerodynamic parameter that represents the drag coefficient of an aircraft when it is producing zero lift. In other words, it is the drag experienced by the aircraft when its lift coefficient (CL) is zero, which occurs when the aircraft is flying in straight and level flight without

The maximum lift-to-drag coefficient, often denoted as (CL/CD)max, is a key performance metric used to assess the aerodynamic efficiency of an aircraft. It represents the highest achievable ratio of the lift coefficient (CL) to the drag coefficient (CD) for a given aircraft configuration, operating condition, and flight regime.  (CL/CD)max is the maximum lift-to-drag ratio e