Induced Drag for Wings having Elliptic Lift Distribution Calculator

✖Lift force is the component of the total force acting on a body that is perpendicular to the direction of the fluid flow.ⓘ Lift Force [F_L]			+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%

✖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 for Wings having Elliptic Lift Distribution [D_i]

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Induced Drag for Wings having Elliptic Lift Distribution Solution

STEP 0: Pre-Calculation Summary

Formula Used

Induced Drag = (Lift Force^2)/(3.14*Dynamic Pressure*Lateral Plane Span^2)
D_i = (F_L^2)/(3.14*q*b_W^2)
This formula uses 4 Variables

Variables Used

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.
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.
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

Lift Force: 2.926 Newton --> 2.926 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

D_i = (F_L^2)/(3.14*q*b_W^2) --> (2.926^2)/(3.14*2.667*15^2)

Evaluating ... ...

D_i = 0.00454373988814031

STEP 3: Convert Result to Output's Unit

0.00454373988814031 Newton --> No Conversion Required

FINAL ANSWER

0.00454373988814031 ≈ 0.004544 Newton <-- Induced Drag

(Calculation completed in 00.007 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

Induced Drag for Wings having Elliptic Lift Distribution Formula

LaTeX Go

Induced Drag = (Lift Force^2)/(3.14*Dynamic Pressure*Lateral Plane Span^2)
D_i = (F_L^2)/(3.14*q*b_W^2)

What is induced drag?

Induced Drag is an inevitable consequence of lift and is produced by the passage of an aerofoil (e.g. wing or tailplane) through the air. Air flowing over the top of a wing tends to flow inwards because the decreased pressure over the top surface is less than the pressure outside the wing tip.

How to Calculate Induced Drag for Wings having Elliptic Lift Distribution?

Induced Drag for Wings having Elliptic Lift Distribution calculator uses Induced Drag = (Lift Force^2)/(3.14*Dynamic Pressure*Lateral Plane Span^2) to calculate the Induced Drag, Induced Drag for Wings having Elliptic Lift Distribution is a measure of the drag force that occurs when a wing produces lift, characterized by an elliptical distribution of lift across the span, and is influenced by the lift force, dynamic pressure, and lateral plane span of the wing. Induced Drag is denoted by D_i symbol.

How to calculate Induced Drag for Wings having Elliptic Lift Distribution using this online calculator? To use this online calculator for Induced Drag for Wings having Elliptic Lift Distribution, enter Lift Force (F_L), Dynamic Pressure (q) & Lateral Plane Span (b_W) and hit the calculate button. Here is how the Induced Drag for Wings having Elliptic Lift Distribution calculation can be explained with given input values -> 0.004544 = (2.926^2)/(3.14*2.667*15^2).

FAQ

What is Induced Drag for Wings having Elliptic Lift Distribution?

Induced Drag for Wings having Elliptic Lift Distribution is a measure of the drag force that occurs when a wing produces lift, characterized by an elliptical distribution of lift across the span, and is influenced by the lift force, dynamic pressure, and lateral plane span of the wing and is represented as D_i = (F_L^2)/(3.14*q*b_W^2) or Induced Drag = (Lift Force^2)/(3.14*Dynamic Pressure*Lateral Plane Span^2). Lift force is the component of the total force acting on a body that is perpendicular to the direction of the fluid flow, 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 Induced Drag for Wings having Elliptic Lift Distribution?

Induced Drag for Wings having Elliptic Lift Distribution is a measure of the drag force that occurs when a wing produces lift, characterized by an elliptical distribution of lift across the span, and is influenced by the lift force, dynamic pressure, and lateral plane span of the wing is calculated using Induced Drag = (Lift Force^2)/(3.14*Dynamic Pressure*Lateral Plane Span^2). To calculate Induced Drag for Wings having Elliptic Lift Distribution, you need Lift Force (F_L), Dynamic Pressure (q) & Lateral Plane Span (b_W). With our tool, you need to enter the respective value for Lift Force, 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 Induced Drag?

In this formula, Induced Drag uses Lift Force, Dynamic Pressure & Lateral Plane Span. We can use 1 other way(s) to calculate the same, which is/are as follows -

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

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