Modern Lift Equation Calculator

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✖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.ⓘ Lift Coefficient [C_L]			+10% -10%
✖Air Density is the density of wind or air in the atmosphere.ⓘ Air Density [ρ_air]			+10% -10%
✖The aircraft gross wing area is the total surface area of both wings of an airplane, including ailerons, flaps, and any other control surfaces.ⓘ Aircraft Gross Wing Area [S]			+10% -10%
✖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.ⓘ Fluid Velocity [u_f]			+10% -10%

✖Lift on Airfoil is component of Resultant Force acting on airfoil perpendicular to freestream Velocity.ⓘ Modern Lift Equation [L]

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Formula

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Modern Lift Equation

Formula

`"L" = ("C"_{"L"}*"ρ"_{"air"}*"S"*"u"_{"f"}^2)/2`

Example

`"2231.46N"=("1.1"*"1.225kg/m³"*"23m²"*("12m/s")^2)/2`

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Modern Lift Equation Solution

STEP 0: Pre-Calculation Summary

Formula Used

Lift on Airfoil = (Lift Coefficient*Air Density*Aircraft Gross Wing Area*Fluid Velocity^2)/2
L = (C_L*ρ_air*S*u_f^2)/2
This formula uses 5 Variables

Variables Used

Lift on Airfoil - (Measured in Newton) - Lift on Airfoil is component of Resultant Force acting on airfoil perpendicular to freestream Velocity.
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.
Air Density - (Measured in Kilogram per Cubic Meter) - Air Density is the density of wind or air in the atmosphere.
Aircraft Gross Wing Area - (Measured in Square Meter) - The aircraft gross wing area is the total surface area of both wings of an airplane, including ailerons, flaps, and any other control surfaces.
Fluid Velocity - (Measured in Meter per Second) - 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.

STEP 1: Convert Input(s) to Base Unit

Lift Coefficient: 1.1 --> No Conversion Required
Air Density: 1.225 Kilogram per Cubic Meter --> 1.225 Kilogram per Cubic Meter No Conversion Required
Aircraft Gross Wing Area: 23 Square Meter --> 23 Square Meter No Conversion Required
Fluid Velocity: 12 Meter per Second --> 12 Meter per Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

L = (C_L*ρ_air*S*u_f^2)/2 --> (1.1*1.225*23*12^2)/2

Evaluating ... ...

L = 2231.46

STEP 3: Convert Result to Output's Unit

2231.46 Newton --> No Conversion Required

FINAL ANSWER

2231.46 Newton <-- Lift on Airfoil

(Calculation completed in 00.020 seconds)

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< 21 Lift and Drag Polar Calculators

Drag Coefficient for given zero-lift drag coefficient

Go Drag Coefficient = Zero-lift drag coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing))

Drag Coefficient for given parasite drag coefficient

Go Drag Coefficient = Parasite Drag coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing))

Coefficient of Drag due to lift

Go Coefficient of drag due to lift = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)

Modern Lift Equation

Go Lift on Airfoil = (Lift Coefficient*Air Density*Aircraft Gross Wing Area*Fluid Velocity^2)/2

Induced drag given span efficiency factor

Go Induced Drag = Drag Coefficient*Density of Material*Velocity^2*Reference Area/2

Lift given induced drag

Go Lift Force = sqrt(Induced Drag*3.14*Dynamic Pressure*Lateral plane span^2)

Induced Drag for Wings having Elliptic Lift Distribution

Go Induced Drag = (Lift Force^2)/(3.14*Dynamic Pressure*Lateral plane span^2)

Coefficient of lift given drag

Go Lift Coefficient = (Gross Weight*Drag Coefficient)/Drag Force

Coefficient of drag given drag

Go Drag Coefficient = (Lift Coefficient*Drag Force)/Gross Weight

Drag

Go Drag Force = Gross Weight/Lift Coefficient/Drag Coefficient

Lift coefficient given drag coefficient

Go Lift Coefficient = Lift Force/Drag Force*Drag Coefficient

Drag coefficient given lift coefficient

Go Drag Coefficient = Lift Coefficient*Drag Force/Lift Force

Lift given drag coefficient

Go Lift Force = Lift Coefficient/Drag Coefficient*Drag Force

Drag given lift coefficient

Go Drag Force = Lift Force*Drag Coefficient/Lift Coefficient

Parasite Drag Coefficient at zero lift

Go Zero-lift drag coefficient = Drag Coefficient-Coefficient of drag due to lift

Lift given lift coefficient

Go Lift Force = Lift Coefficient*Dynamic Pressure

Drag given drag coefficient

Go Drag Force = Drag Coefficient*Dynamic Pressure

Lift coefficient new

Go Lift Coefficient = Lift Force/Dynamic Pressure

Drag coefficient new

Go Drag Coefficient = Drag Force/Dynamic Pressure

Lift given aerodynamic force

Go Lift Force = Aerodynamic Force-Drag Force

Drag given aerodynamic force

Go Drag Force = Aerodynamic Force-Lift Force

Modern Lift Equation Formula

Lift on Airfoil = (Lift Coefficient*Air Density*Aircraft Gross Wing Area*Fluid Velocity^2)/2
L = (C_L*ρ_air*S*u_f^2)/2

What is 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.

What is Wing Area?

The wing area is a projected area and is almost half of the total surface area. In aerodynamics, the surface area of a wing is calculated by looking at the wing from a top-down view and measuring the area of the wing. This surface area is also known as the planform area.

How to Calculate Modern Lift Equation?

Modern Lift Equation calculator uses Lift on Airfoil = (Lift Coefficient*Air Density*Aircraft Gross Wing Area*Fluid Velocity^2)/2 to calculate the Lift on Airfoil, The Modern Lift Equation states that lift L is equal to the lift coefficient times the air-density times half of the velocity squared times the wing area. Lift on Airfoil is denoted by L symbol.

How to calculate Modern Lift Equation using this online calculator? To use this online calculator 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. Here is how the Modern Lift Equation calculation can be explained with given input values -> 2231.46 = (1.1*1.225*23*12^2)/2.

FAQ

What is Modern Lift Equation?

The Modern Lift Equation states that lift L is equal to the lift coefficient times the air-density times half of the velocity squared times the wing area and is represented as L = (C_L*ρ_air*S*u_f^2)/2 or Lift on Airfoil = (Lift Coefficient*Air Density*Aircraft Gross Wing Area*Fluid Velocity^2)/2. 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, Air Density is the density of wind or air in the atmosphere, The aircraft gross wing area is the total surface area of both wings of an airplane, including ailerons, flaps, and any other control surfaces & 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.

How to calculate Modern Lift Equation?

The Modern Lift Equation states that lift L is equal to the lift coefficient times the air-density times half of the velocity squared times the wing area is calculated using Lift on Airfoil = (Lift Coefficient*Air Density*Aircraft Gross Wing Area*Fluid Velocity^2)/2. To calculate Modern Lift Equation, you need Lift Coefficient (C_L), Air Density (ρ_air), Aircraft Gross Wing Area (S) & Fluid Velocity (u_f). With our tool, you need to enter the respective value for Lift Coefficient, Air Density, Aircraft Gross Wing Area & Fluid Velocity and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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