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Modern Lift Equation Formula

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Lift on Airfoil is component of Resultant Force acting on airfoil perpendicular to freestream Velocity. Check FAQs

L = \frac{C L \cdot ρ air \cdot S \cdot {u f}^{2}}{2}

L - Lift on Airfoil?C_L - Lift Coefficient?ρ_air - Air Density?S - Aircraft Gross Wing Area?u_f - Fluid Velocity?

Modern Lift Equation Example

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Here is how the Modern Lift Equation equation looks like with Values.

Here is how the Modern Lift Equation equation looks like with Units.

Here is how the Modern Lift Equation equation looks like.

2231.46 = \frac{1.1 \cdot 1.225 \cdot 23 \cdot 12^{2}}{2}

2231.46N = \frac{1.1 \cdot 1.225kg/m³ \cdot 23m² \cdot {12m/s}^{2}}{2}

2231.46 = \frac{1.1 \cdot 1.225 \cdot 23 \cdot 12^{2}}{2}

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Modern Lift Equation Solution

Follow our step by step solution on how to calculate Modern Lift Equation?

FIRST Step Consider the formula

L = \frac{C L \cdot ρ air \cdot S \cdot {u f}^{2}}{2}

Next Step Substitute values of Variables

∴

L = \frac{1.1 \cdot 1.225kg/m³ \cdot 23m² \cdot {12m/s}^{2}}{2}

Next Step Prepare to Evaluate

∴

L = \frac{1.1 \cdot 1.225 \cdot 23 \cdot 12^{2}}{2}

LAST Step Evaluate

∴

L = 2231.46N

Modern Lift Equation Formula Elements

Variables

Lift on Airfoil

Lift on Airfoil is component of Resultant Force acting on airfoil perpendicular to freestream Velocity.

Symbol: L

Measurement: ForceUnit: N

Note: Value can be positive or negative.

Formulas to find Lift on Airfoil

Lift Coefficient

The Lift Coefficient is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area.

Symbol: C_L

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Lift Coefficient

Air Density

Air Density is the density of wind or air in the atmosphere.

Symbol: ρ_air

Measurement: DensityUnit: kg/m³

Note: Value should be greater than 0.

Formulas to find Air Density

Aircraft Gross Wing Area

The aircraft gross wing area is the total surface area of both wings of an airplane, including ailerons, flaps, and any other control surfaces.

Symbol: S

Measurement: AreaUnit: m²

Note: Value can be positive or negative.

Formulas to find Aircraft Gross Wing Area

Fluid Velocity

Fluid velocity is a vector quantity in aerodynamics that describes the magnitude and direction of a fluid's motion at a specific point in space and time.

Symbol: u_f

Measurement: SpeedUnit: m/s

Note: Value can be positive or negative.

Formulas to find Fluid Velocity

Other formulas in Lift and Drag Polar category

Go Drag Coefficient for given parasite drag coefficient

C D = C D,e + (\frac{{C L}^{2}}{π \cdot e oswald \cdot AR})

Go Drag Coefficient for given zero-lift drag coefficient

C D = C D,0 + (\frac{{C L}^{2}}{π \cdot e oswald \cdot AR})

Go Coefficient of Drag due to lift

C D,i = \frac{{C L}^{2}}{π \cdot e oswald \cdot AR}

Go Parasite Drag Coefficient at zero lift

C D,0 = C D - C D,i

How to Evaluate Modern Lift Equation?

Modern Lift Equation evaluator uses Lift on Airfoil = (Lift Coefficient*Air Density*Aircraft Gross Wing Area*Fluid Velocity^2)/2 to evaluate the Lift on Airfoil, The Modern Lift Equation is a measure of the upward force exerted on an object, such as an airplane wing, as it moves through the air, resulting from the interaction between the air and the wing's surface. It is an essential concept in aerodynamics, allowing engineers to design and optimize wing shapes for efficient flight. Lift on Airfoil is denoted by L symbol.

How to evaluate Modern Lift Equation using this online evaluator? To use this online evaluator for Modern Lift Equation, enter Lift Coefficient (C_L), Air Density (ρ_air), Aircraft Gross Wing Area (S) & Fluid Velocity (u_f) and hit the calculate button.

FAQs on Modern Lift Equation

What is the formula to find Modern Lift Equation?

The formula of Modern Lift Equation is expressed as Lift on Airfoil = (Lift Coefficient*Air Density*Aircraft Gross Wing Area*Fluid Velocity^2)/2. Here is an example- 2231.46 = (1.1*1.225*23*12^2)/2.

How to calculate Modern Lift Equation?

With Lift Coefficient (C_L), Air Density (ρ_air), Aircraft Gross Wing Area (S) & Fluid Velocity (u_f) we can find Modern Lift Equation using the formula - Lift on Airfoil = (Lift Coefficient*Air Density*Aircraft Gross Wing Area*Fluid Velocity^2)/2.

Can the Modern Lift Equation be negative?

Yes, the Modern Lift Equation, measured in Force can be negative.

Which unit is used to measure Modern Lift Equation?

Modern Lift Equation is usually measured using the Newton[N] for Force. Exanewton[N], Meganewton[N], Kilonewton[N] are the few other units in which Modern Lift Equation can be measured.

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Modern Lift Equation Formula

Modern Lift Equation Example

Modern Lift Equation Solution

Modern Lift Equation Formula Elements

Other formulas in Lift and Drag Polar category

How to Evaluate Modern Lift Equation?

FAQs on Modern Lift Equation

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