The lift-dependent drag coefficient (CDi) is a component of the total drag coefficient (CD) and represents the drag that is directly proportional to the lift being generated by the aircraft. It is also known as induced drag and is primarily caused by the production of lift. The formula for calculating the lift-dependent drag coefficient (CDi) […]
Lift-Dependant Drag Coefficient (CDi) Calculator Read More »
The parasite drag coefficient (CD0) is a parameter used in aircraft design and aerodynamics to quantify the drag produced by an aircraft when it is in a clean configuration (without flaps or other high-lift devices) and at a specified flight condition (e.g., cruise). It represents the non-lift-dependent drag that opposes the aircraft’s motion through the
Parasite Drag Coefficient Calculator Read More »
The lift coefficient at maximum lift-to-drag ratio (CLmax) represents the lift coefficient at which an aircraft achieves its maximum aerodynamic efficiency. This efficiency point is crucial for optimizing an aircraft’s performance, especially during cruising conditions when minimizing drag and maximizing lift are essential for fuel efficiency. The formula for calculating CLmax is as follows: CLmax
Lift Coefficient At Maximum Lift-To-Drag Ratio Calculator Read More »
The drag polar is a graphical representation used in aircraft design and aerodynamics to depict the relationship between an aircraft’s drag coefficient (CD) and its lift coefficient (CL) at various flight conditions. It provides valuable insights into an aircraft’s aerodynamic performance, particularly in terms of drag and lift characteristics. The drag polar is typically represented
Drag Polar Calculator Read More »
The ratio of temperatures behind the wave to the ahead of the wave is a measure of the change in temperature that occurs when a fluid flows across a wave, such as a shock wave or an expansion wave. The temperature ratio is defined as the ratio of the temperature behind the wave (T2) to
Ratio of temperatures behind the wave to the ahead of the wave Calculator Read More »
The ratio of density behind the wave to the density ahead of the wave is a measure of the change in density that occurs when a fluid flows across a wave, such as a shock wave or an expansion wave. The density ratio is defined as the ratio of the density behind the wave (ρ2)
Ratio of density behind the wave to the density ahead of the wave Calculator Read More »
The pressure ratio across the wave (p2/p1) is a measure of the change in pressure that occurs when a fluid flows across a wave, such as a shock wave or an expansion wave. The pressure ratio is defined as the ratio of the pressure behind the wave (p2) to the pressure ahead of the wave
Pressure ratio across the wave when Mach number goes to infinity Calculator Read More »
The root chord of an exposed wing, often denoted as croot, is the chord length of the wing at its innermost section, typically where the wing attaches to the fuselage. It is one of the key geometric parameters of the wing and plays a crucial role in determining the aircraft’s aerodynamic characteristics. The formula for
Root Chord of Exposed Wing Calculator Read More »
The local chord (c) of an aircraft’s wing is the length of a straight line segment from the leading edge to the trailing edge of the wing at a specific point along the wing’s span. It is a critical parameter in aerodynamics and aircraft design because it determines the wing’s geometry and influences various aerodynamic
local chord (c) Calculator Read More »
Aerodynamic balance, often denoted as AB, is a parameter used in aircraft design to assess the balance between aerodynamic forces acting on an aircraft’s control surfaces and the moments created by those forces around the aircraft’s center of gravity (CG). It helps designers ensure that control surfaces are correctly sized and positioned for stable and
Aerodynamic Balance Calculator Read More »
