Aerodynamics Calculator

The pressure behind a shock wave, often denoted as p2​, refers to the pressure of a fluid immediately after it has passed through a shock wave in a compressible flow. The pressure behind the shock wave is typically higher than the pressure upstream of the shock. This is because the shock wave slows down the […]

The specific enthalpy behind a shock wave refers to the enthalpy of a fluid immediately after it has passed through a shock wave in a compressible flow. Enthalpy is a thermodynamic property that combines the internal energy of a fluid with the work done on or by the fluid due to its pressure and volume

Bernoulli’s principle is a fundamental concept in fluid dynamics that describes the relationship between the pressure, velocity, and elevation of a fluid in motion. It states that within an inviscid (non-viscous) and incompressible fluid flow, an increase in the fluid’s velocity is accompanied by a decrease in its pressure, and vice versa.  p represents the

Velocity at point one on the airfoil (V1​) refers to the local velocity of the fluid at a specific location on or near an airfoil’s surface. In fluid dynamics, the velocity of the fluid is a fundamental parameter that describes how fast the fluid is moving at a particular point. Mach number (M1) Speed of

Speed of sound at point one on the airfoil refers to the local speed at which pressure waves or sound waves propagate through the fluid at a specific location on or near an airfoil’s surface. In other words, it’s the speed at which disturbances in pressure, velocity, or density travel through the fluid near the

Temperature at point one on the airfoil (T1​) typically refers to the local temperature of the air or fluid at a specific point on an airfoil’s surface or in its vicinity. Airfoil is the cross-sectional shape of an aircraft wing, and during aerodynamic analysis, various parameters like pressure, velocity, and temperature are measured at different

The term “freestream total pressure” (p0​,∞) refers to the total pressure of a fluid in the undisturbed flow far away from any significant sources of pressure changes or disturbances. It represents the pressure that the fluid would experience if it were brought to rest isentropically (without any losses due to friction or heat transfer) from

The characteristic Mach number, often denoted as M∗, is a dimensionless parameter used in fluid dynamics to describe the behavior of compressible flows, particularly when analyzing the effects of compressibility on fluid properties.  Characteristic Mach number (M*)  Local Mach number (M)  Specific heat ratio (γ)

The local Mach number (M) is a dimensionless parameter used in fluid dynamics to describe the relative velocity of a fluid flow compared to the local speed of sound in that fluid at a specific point.  Specific heat ratio (γ)  Characteristic Mach Number (M*)  Local Mach Number (M) 

The speed of sound at sonic conditions, often denoted as a∗, refers to the speed of sound in a fluid when the fluid flow is precisely at the speed of sound, which is also known as “sonic velocity.”  Speed of sound at sonic condition (a*) in m/s Temperature at sonic conditions (T*) in K Specific