Lift given induced drag Calculator

✖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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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: 0.004544 Newton --> 0.004544 Newton No Conversion Required
Dynamic Pressure: 2.667 Pascal --> 2.667 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(0.004544*3.14*2.667*15^2)

Evaluating ... ...

F_L = 2.9260837499976

STEP 3: Convert Result to Output's Unit

2.9260837499976 Newton --> No Conversion Required

FINAL ANSWER

2.9260837499976 ≈ 2.926084 Newton <-- Lift Force

(Calculation completed in 00.020 seconds)

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Created by Himanshu Sharma

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

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< Lift and Drag Polar Calculators

Drag Coefficient for given zero-lift drag coefficient

LaTeX 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

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

Coefficient of Drag due to lift

LaTeX Go Coefficient of Drag due to Lift = (Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing)

Parasite Drag Coefficient at zero lift

LaTeX Go Zero-Lift Drag Coefficient = Drag Coefficient-Coefficient of Drag due to Lift

Lift given induced drag Formula

LaTeX Go

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, Lift Given Induced Drag is a measure of the upward force exerted on an airfoil, calculated by considering the induced drag, dynamic pressure, and lateral plane span, which helps in understanding the aerodynamic performance of an aircraft or wing design. 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 -> 2.745349 = sqrt(0.004544*3.14*2.667*15^2).

FAQ

What is Lift given induced drag?

Lift Given Induced Drag is a measure of the upward force exerted on an airfoil, calculated by considering the induced drag, dynamic pressure, and lateral plane span, which helps in understanding the aerodynamic performance of an aircraft or wing design 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?

Lift Given Induced Drag is a measure of the upward force exerted on an airfoil, calculated by considering the induced drag, dynamic pressure, and lateral plane span, which helps in understanding the aerodynamic performance of an aircraft or wing design 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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