Lift given induced drag Calculator

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Lift and Drag Polar

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✖Induced drag is primarily caused by the formation of wingtip vortices, which are created due to the pressure difference between the upper and lower surfaces of a lifting wing.ⓘ Induced Drag [D_i]			+10% -10%
✖Dynamic pressure, also referred to as velocity pressure, is a specific type of pressure associated with the kinetic energy per unit volume of a moving fluid.ⓘ Dynamic Pressure [q]			+10% -10%
✖Lateral plane span is set of all linear combinations of 2 non-parallel vectors u and v is called the span of u and v.ⓘ Lateral plane span [b_W]			+10% -10%

✖Lift force is the component of the total force acting on a body that is perpendicular to the direction of the fluid flow.ⓘ Lift given induced drag [F_L]

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Formula

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Lift given induced drag

Formula

`"F"_{"L"} = sqrt("D"_{"i"}*3.14*"q"*"b"_{"W"}^2)`

Example

`"844.7278N"=sqrt("101N"*3.14*"10Pa"*("15m")^2)`

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Lift given induced drag Solution

STEP 0: Pre-Calculation Summary

Formula Used

Lift Force = sqrt(Induced Drag*3.14*Dynamic Pressure*Lateral plane span^2)
F_L = sqrt(D_i*3.14*q*b_W^2)
This formula uses 1 Functions, 4 Variables

Functions Used

sqrt - A square root function is a function that takes a non-negative number as an input and returns the square root of the given input number., sqrt(Number)

Variables Used

Lift Force - (Measured in Newton) - Lift force is the component of the total force acting on a body that is perpendicular to the direction of the fluid flow.
Induced Drag - (Measured in Newton) - Induced drag is primarily caused by the formation of wingtip vortices, which are created due to the pressure difference between the upper and lower surfaces of a lifting wing.
Dynamic Pressure - (Measured in Pascal) - Dynamic pressure, also referred to as velocity pressure, is a specific type of pressure associated with the kinetic energy per unit volume of a moving fluid.
Lateral plane span - (Measured in Meter) - Lateral plane span is set of all linear combinations of 2 non-parallel vectors u and v is called the span of u and v.

STEP 1: Convert Input(s) to Base Unit

Induced Drag: 101 Newton --> 101 Newton No Conversion Required
Dynamic Pressure: 10 Pascal --> 10 Pascal No Conversion Required
Lateral plane span: 15 Meter --> 15 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

F_L = sqrt(D_i*3.14*q*b_W^2) --> sqrt(101*3.14*10*15^2)

Evaluating ... ...

F_L = 844.727766798274

STEP 3: Convert Result to Output's Unit

844.727766798274 Newton --> No Conversion Required

FINAL ANSWER

844.727766798274 ≈ 844.7278 Newton <-- Lift Force

(Calculation completed in 00.004 seconds)

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National Institute of Technology, Hamirpur (NITH), Himachal Pradesh

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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

Lift given induced drag Formula

Lift Force = sqrt(Induced Drag*3.14*Dynamic Pressure*Lateral plane span^2)
F_L = sqrt(D_i*3.14*q*b_W^2)

What is lift force?

A fluid flowing around an object exerts a force on it. Lift is the component of this force that is perpendicular to the oncoming flow direction. It contrasts with the drag force, which is the component of the force parallel to the flow direction.

How to Calculate Lift given induced drag?

Lift given induced drag calculator uses Lift Force = sqrt(Induced Drag*3.14*Dynamic Pressure*Lateral plane span^2) to calculate the Lift Force, The Lift given induced drag formula is defined as the amount of contrasting force to the weight of the plane that helps in creating the lift in airplane in the presence of drag. Lift Force is denoted by F_L symbol.

How to calculate Lift given induced drag using this online calculator? To use this online calculator for Lift given induced drag, enter Induced Drag (D_i), Dynamic Pressure (q) & Lateral plane span (b_W) and hit the calculate button. Here is how the Lift given induced drag calculation can be explained with given input values -> 844.7278 = sqrt(101*3.14*10*15^2).

FAQ

What is Lift given induced drag?

The Lift given induced drag formula is defined as the amount of contrasting force to the weight of the plane that helps in creating the lift in airplane in the presence of drag and is represented as F_L = sqrt(D_i*3.14*q*b_W^2) or Lift Force = sqrt(Induced Drag*3.14*Dynamic Pressure*Lateral plane span^2). Induced drag is primarily caused by the formation of wingtip vortices, which are created due to the pressure difference between the upper and lower surfaces of a lifting wing, Dynamic pressure, also referred to as velocity pressure, is a specific type of pressure associated with the kinetic energy per unit volume of a moving fluid & Lateral plane span is set of all linear combinations of 2 non-parallel vectors u and v is called the span of u and v.

How to calculate Lift given induced drag?

The Lift given induced drag formula is defined as the amount of contrasting force to the weight of the plane that helps in creating the lift in airplane in the presence of drag is calculated using Lift Force = sqrt(Induced Drag*3.14*Dynamic Pressure*Lateral plane span^2). To calculate Lift given induced drag, you need Induced Drag (D_i), Dynamic Pressure (q) & Lateral plane span (b_W). With our tool, you need to enter the respective value for Induced Drag, Dynamic Pressure & Lateral plane span and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Lift Force?

In this formula, Lift Force uses Induced Drag, Dynamic Pressure & Lateral plane span. We can use 3 other way(s) to calculate the same, which is/are as follows -

Lift Force = Lift Coefficient*Dynamic Pressure
Lift Force = Lift Coefficient/Drag Coefficient*Drag Force
Lift Force = Aerodynamic Force-Drag Force

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