Induced Drag Coefficient given Aspect Ratio Calculator

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Two-Dimensional Incompressible Flow

Compressible Flow

Fundamentals of Inviscid and Incompressible Flow

Three-Dimensional Incompressible Flow

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Lift Distribution

Elementary Flows

Flow and Lift Distribution

Flow over Airfoils and Wings

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Elliptical Lift Distribution

General Lift Distribution

✖The Lift Coefficient ELD 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 ELD [C_L,ELD]			+10% -10%
✖Wing Aspect Ratio ELD is defined as the ratio of the square of wingspan to the wing area or wingspan over wing chord for a rectangular planform.ⓘ Wing Aspect Ratio ELD [AR_ELD]			+10% -10%

✖The Induced Drag Coefficient ELD is a dimensionless parameter that describes a relation between the coefficient of the lift and the aspect ratio.ⓘ Induced Drag Coefficient given Aspect Ratio [C_D,i,ELD]

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Formula

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Induced Drag Coefficient given Aspect Ratio

Formula

`"C"_{"D,i,ELD"} = "C"_{"L,ELD"}^2/(pi*"AR"_{"ELD"})`

Example

`"0.284952"=("1.49")^2/(pi*"2.48")`

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Induced Drag Coefficient given Aspect Ratio Solution

STEP 0: Pre-Calculation Summary

Formula Used

Induced Drag Coefficient ELD = Lift Coefficient ELD^2/(pi*Wing Aspect Ratio ELD)
C_D,i,ELD = C_L,ELD^2/(pi*AR_ELD)
This formula uses 1 Constants, 3 Variables

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Variables Used

Induced Drag Coefficient ELD - The Induced Drag Coefficient ELD is a dimensionless parameter that describes a relation between the coefficient of the lift and the aspect ratio.
Lift Coefficient ELD - The Lift Coefficient ELD 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.
Wing Aspect Ratio ELD - Wing Aspect Ratio ELD is defined as the ratio of the square of wingspan to the wing area or wingspan over wing chord for a rectangular planform.

STEP 1: Convert Input(s) to Base Unit

Lift Coefficient ELD: 1.49 --> No Conversion Required
Wing Aspect Ratio ELD: 2.48 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_D,i,ELD = C_L,ELD^2/(pi*AR_ELD) --> 1.49^2/(pi*2.48)

Evaluating ... ...

C_D,i,ELD = 0.284951523514772

STEP 3: Convert Result to Output's Unit

0.284951523514772 --> No Conversion Required

FINAL ANSWER

0.284951523514772 ≈ 0.284952 <-- Induced Drag Coefficient ELD

(Calculation completed in 00.004 seconds)

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< 20 Elliptical Lift Distribution Calculators

Lift at given Distance along Wingspan

Go Lift at Distance = Freestream Density*Freestream Velocity*Circulation at Origin*sqrt(1-(2*Distance from Center to Point/Wingspan)^2)

Circulation at Origin in Elliptical Lift Distribution

Go Circulation at Origin = 2*Freestream Velocity*Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan)

Coefficient of Lift given Circulation at Origin

Go Lift Coefficient ELD = pi*Wingspan*Circulation at Origin/(2*Freestream Velocity*Reference Area Origin)

Freestream Velocity given Circulation at Origin

Go Freestream Velocity = pi*Wingspan*Circulation at Origin/(2*Reference Area Origin*Lift Coefficient ELD)

Lift of Wing given Circulation at Origin

Go Lift Force = (pi*Freestream Density*Freestream Velocity*Wingspan*Circulation at Origin)/4

Circulation at Origin given Lift of Wing

Go Circulation at Origin = 4*Lift Force/(Freestream Density*Freestream Velocity*Wingspan*pi)

Induced Angle of Attack given Coefficient of Lift

Go Induced Angle of Attack = Reference Area Origin*Lift Coefficient Origin/(pi*Wingspan^2)

Circulation at given Distance along Wingspan

Go Circulation = Circulation at Origin*sqrt(1-(2*Distance from Center to Point/Wingspan)^2)

Coefficient of Lift given Induced Drag Coefficient

Go Lift Coefficient ELD = sqrt(pi*Wing Aspect Ratio ELD*Induced Drag Coefficient ELD)

Aspect Ratio given Induced Drag Coefficient

Go Wing Aspect Ratio ELD = Lift Coefficient ELD^2/(pi*Induced Drag Coefficient ELD)

Induced Drag Coefficient given Aspect Ratio

Go Induced Drag Coefficient ELD = Lift Coefficient ELD^2/(pi*Wing Aspect Ratio ELD)

Induced Angle of Attack given Circulation at Origin

Go Induced Angle of Attack = Circulation at Origin/(2*Wingspan*Freestream Velocity)

Freestream Velocity given Induced Angle of Attack

Go Freestream Velocity = Circulation at Origin/(2*Wingspan*Induced Angle of Attack)

Circulation at Origin given Induced Angle of Attack

Go Circulation at Origin = 2*Wingspan*Induced Angle of Attack*Freestream Velocity

Induced Angle of Attack given Aspect Ratio

Go Induced Angle of Attack = Lift Coefficient Origin/(pi*Wing Aspect Ratio ELD)

Aspect Ratio given Induced Angle of Attack

Go Wing Aspect Ratio ELD = Lift Coefficient ELD/(pi*Induced Angle of Attack)

Coefficient of Lift given Induced Angle of Attack

Go Lift Coefficient ELD = pi*Induced Angle of Attack*Wing Aspect Ratio ELD

Induced Angle of Attack given Downwash

Go Induced Angle of Attack = -(Downwash/Freestream Velocity)

Downwash in Elliptical Lift Distribution

Go Downwash = -Circulation at Origin/(2*Wingspan)

Circulation at Origin given Downwash

Go Circulation at Origin = -2*Downwash*Wingspan

Induced Drag Coefficient given Aspect Ratio Formula

Induced Drag Coefficient ELD = Lift Coefficient ELD^2/(pi*Wing Aspect Ratio ELD)
C_D,i,ELD = C_L,ELD^2/(pi*AR_ELD)

Do winglets reduce induced drag?

Winglets increase an aircraft's operating efficiency by reducing what is called induced drag at the tips of the wings. An aircraft's wing is shaped to generate negative pressure on the upper surface and positive pressure on the lower surface as the aircraft moves forward.

How to Calculate Induced Drag Coefficient given Aspect Ratio?

Induced Drag Coefficient given Aspect Ratio calculator uses Induced Drag Coefficient ELD = Lift Coefficient ELD^2/(pi*Wing Aspect Ratio ELD) to calculate the Induced Drag Coefficient ELD, The Induced drag coefficient given aspect ratio formula calculates the coefficient of induced drag which has been caused due to the element of the air deflected downward which is not vertical to the flight path but is tilted slightly rearward from it. Induced Drag Coefficient ELD is denoted by C_D,i,ELD symbol.

How to calculate Induced Drag Coefficient given Aspect Ratio using this online calculator? To use this online calculator for Induced Drag Coefficient given Aspect Ratio, enter Lift Coefficient ELD (C_L,ELD) & Wing Aspect Ratio ELD (AR_ELD) and hit the calculate button. Here is how the Induced Drag Coefficient given Aspect Ratio calculation can be explained with given input values -> 0.288789 = 1.49^2/(pi*2.48).

FAQ

What is Induced Drag Coefficient given Aspect Ratio?

The Induced drag coefficient given aspect ratio formula calculates the coefficient of induced drag which has been caused due to the element of the air deflected downward which is not vertical to the flight path but is tilted slightly rearward from it and is represented as C_D,i,ELD = C_L,ELD^2/(pi*AR_ELD) or Induced Drag Coefficient ELD = Lift Coefficient ELD^2/(pi*Wing Aspect Ratio ELD). The Lift Coefficient ELD 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 & Wing Aspect Ratio ELD is defined as the ratio of the square of wingspan to the wing area or wingspan over wing chord for a rectangular planform.

How to calculate Induced Drag Coefficient given Aspect Ratio?

The Induced drag coefficient given aspect ratio formula calculates the coefficient of induced drag which has been caused due to the element of the air deflected downward which is not vertical to the flight path but is tilted slightly rearward from it is calculated using Induced Drag Coefficient ELD = Lift Coefficient ELD^2/(pi*Wing Aspect Ratio ELD). To calculate Induced Drag Coefficient given Aspect Ratio, you need Lift Coefficient ELD (C_L,ELD) & Wing Aspect Ratio ELD (AR_ELD). With our tool, you need to enter the respective value for Lift Coefficient ELD & Wing Aspect Ratio ELD 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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