Induced Drag Coefficient given Induced Drag Factor 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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General Lift Distribution

Elliptical Lift Distribution

✖The Induced Drag Factor is a function of the Fourier series constants which has been used for the general circulation distribution expression for the finite wing.ⓘ Induced Drag Factor [δ]			+10% -10%
✖The Lift Coefficient GLD 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 GLD [C_L,GLD]			+10% -10%
✖Wing Aspect Ratio GLD 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 GLD [AR_GLD]			+10% -10%

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

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Formula

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Induced Drag Coefficient given Induced Drag Factor

Formula

`"C"_{"D,i,GLD"} = ((1+"δ")*"C"_{"L,GLD"}^2)/(pi*"AR"_{"GLD"})`

Example

`"0.048149"=((1+"0.05")*("1.47")^2)/(pi*"15")`

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Induced Drag Coefficient given Induced Drag Factor Solution

STEP 0: Pre-Calculation Summary

Formula Used

Induced Drag Coefficient GLD = ((1+Induced Drag Factor)*Lift Coefficient GLD^2)/(pi*Wing Aspect Ratio GLD)
C_D,i,GLD = ((1+δ)*C_L,GLD^2)/(pi*AR_GLD)
This formula uses 1 Constants, 4 Variables

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Variables Used

Induced Drag Coefficient GLD - The Induced Drag Coefficient GLD is a dimensionless parameter that describes a relation between the coefficient of the lift and the aspect ratio.
Induced Drag Factor - The Induced Drag Factor is a function of the Fourier series constants which has been used for the general circulation distribution expression for the finite wing.
Lift Coefficient GLD - The Lift Coefficient GLD 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 GLD - Wing Aspect Ratio GLD 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

Induced Drag Factor: 0.05 --> No Conversion Required
Lift Coefficient GLD: 1.47 --> No Conversion Required
Wing Aspect Ratio GLD: 15 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_D,i,GLD = ((1+δ)*C_L,GLD^2)/(pi*AR_GLD) --> ((1+0.05)*1.47^2)/(pi*15)

Evaluating ... ...

C_D,i,GLD = 0.0481485083138187

STEP 3: Convert Result to Output's Unit

0.0481485083138187 --> No Conversion Required

FINAL ANSWER

0.0481485083138187 ≈ 0.048149 <-- Induced Drag Coefficient GLD

(Calculation completed in 00.004 seconds)

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Induced Lift Slope Factor given Lift Curve Slope of Finite Wing

Go Induced Lift Slope Factor of Finite Wing = (pi*Wing Aspect Ratio GLD*(2D Lift Curve Slope/Lift Curve Slope-1))/2D Lift Curve Slope-1

Lift Coefficient given Induced Drag Factor

Go Lift Coefficient GLD = sqrt((pi*Wing Aspect Ratio GLD*Induced Drag Coefficient GLD)/(1+Induced Drag Factor))

Lift Coefficient given Span Efficiency Factor

Go Lift Coefficient GLD = sqrt(pi*Span Efficiency Factor*Wing Aspect Ratio GLD*Induced Drag Coefficient GLD)

Induced Drag Coefficient given Induced Drag Factor

Go Induced Drag Coefficient GLD = ((1+Induced Drag Factor)*Lift Coefficient GLD^2)/(pi*Wing Aspect Ratio GLD)

Aspect Ratio given Induced Drag Factor

Go Wing Aspect Ratio GLD = ((1+Induced Drag Factor)*Lift Coefficient GLD^2)/(pi*Induced Drag Coefficient GLD)

Induced Drag Coefficient given Span Efficiency Factor

Go Induced Drag Coefficient GLD = Lift Coefficient GLD^2/(pi*Span Efficiency Factor*Wing Aspect Ratio GLD)

Span Efficiency Factor given Induced Drag Coefficient

Go Span Efficiency Factor = Lift Coefficient GLD^2/(pi*Wing Aspect Ratio GLD*Induced Drag Coefficient GLD)

Induced Drag Factor given Induced Drag Coefficient

Go Induced Drag Factor = (pi*Wing Aspect Ratio GLD*Induced Drag Coefficient GLD)/Lift Coefficient GLD^2-1

Span Efficiency Factor

Go Span Efficiency Factor = (1+Induced Drag Factor)^(-1)

Induced Drag Factor given Span Efficiency Factor

Go Induced Drag Factor = Span Efficiency Factor^(-1)-1

Induced Drag Coefficient given Induced Drag Factor Formula

Induced Drag Coefficient GLD = ((1+Induced Drag Factor)*Lift Coefficient GLD^2)/(pi*Wing Aspect Ratio GLD)
C_D,i,GLD = ((1+δ)*C_L,GLD^2)/(pi*AR_GLD)

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 Induced Drag Factor?

Induced Drag Coefficient given Induced Drag Factor calculator uses Induced Drag Coefficient GLD = ((1+Induced Drag Factor)*Lift Coefficient GLD^2)/(pi*Wing Aspect Ratio GLD) to calculate the Induced Drag Coefficient GLD, The Induced drag coefficient given induced drag factor 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 GLD is denoted by C_D,i,GLD symbol.

How to calculate Induced Drag Coefficient given Induced Drag Factor using this online calculator? To use this online calculator for Induced Drag Coefficient given Induced Drag Factor, enter Induced Drag Factor (δ), Lift Coefficient GLD (C_L,GLD) & Wing Aspect Ratio GLD (AR_GLD) and hit the calculate button. Here is how the Induced Drag Coefficient given Induced Drag Factor calculation can be explained with given input values -> 0.048149 = ((1+0.05)*1.47^2)/(pi*15).

FAQ

What is Induced Drag Coefficient given Induced Drag Factor?

The Induced drag coefficient given induced drag factor 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,GLD = ((1+δ)*C_L,GLD^2)/(pi*AR_GLD) or Induced Drag Coefficient GLD = ((1+Induced Drag Factor)*Lift Coefficient GLD^2)/(pi*Wing Aspect Ratio GLD). The Induced Drag Factor is a function of the Fourier series constants which has been used for the general circulation distribution expression for the finite wing, The Lift Coefficient GLD 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 GLD 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 Induced Drag Factor?

The Induced drag coefficient given induced drag factor 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 GLD = ((1+Induced Drag Factor)*Lift Coefficient GLD^2)/(pi*Wing Aspect Ratio GLD). To calculate Induced Drag Coefficient given Induced Drag Factor, you need Induced Drag Factor (δ), Lift Coefficient GLD (C_L,GLD) & Wing Aspect Ratio GLD (AR_GLD). With our tool, you need to enter the respective value for Induced Drag Factor, Lift Coefficient GLD & Wing Aspect Ratio GLD 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 Coefficient GLD?

In this formula, Induced Drag Coefficient GLD uses Induced Drag Factor, Lift Coefficient GLD & Wing Aspect Ratio GLD. We can use 1 other way(s) to calculate the same, which is/are as follows -

Induced Drag Coefficient GLD = Lift Coefficient GLD^2/(pi*Span Efficiency Factor*Wing Aspect Ratio GLD)

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