Induced Drag Factor given Induced Drag Coefficient Calculator

✖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 GLD [C_D,i,GLD]			+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%

✖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 given Induced Drag Coefficient [δ]

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Induced Drag Factor given Induced Drag Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Variables Used

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.
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.
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.
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.

STEP 1: Convert Input(s) to Base Unit

Wing Aspect Ratio GLD: 15 --> No Conversion Required
Induced Drag Coefficient GLD: 0.048 --> No Conversion Required
Lift Coefficient GLD: 1.47 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

δ = (pi*AR_GLD*C_D,i,GLD)/C_L,GLD^2-1 --> (pi*15*0.048)/1.47^2-1

Evaluating ... ...

δ = 0.046761400613009

STEP 3: Convert Result to Output's Unit

0.046761400613009 --> No Conversion Required

FINAL ANSWER

0.046761400613009 ≈ 0.046761 <-- Induced Drag Factor

(Calculation completed in 00.004 seconds)

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< General Lift Distribution Calculators

Lift Coefficient given Span Efficiency Factor

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

Induced Drag Coefficient given Span Efficiency Factor

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

Span Efficiency Factor

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

Induced Drag Factor given Span Efficiency Factor

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

Induced Drag Factor given Induced Drag Coefficient Formula

LaTeX Go

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

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 Factor given Induced Drag Coefficient?

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

How to calculate Induced Drag Factor given Induced Drag Coefficient using this online calculator? To use this online calculator for Induced Drag Factor given Induced Drag Coefficient, enter Wing Aspect Ratio GLD (AR_GLD), Induced Drag Coefficient GLD (C_D,i,GLD) & Lift Coefficient GLD (C_L,GLD) and hit the calculate button. Here is how the Induced Drag Factor given Induced Drag Coefficient calculation can be explained with given input values -> -0.127699 = (pi*15*0.048)/1.47^2-1.

FAQ

What is Induced Drag Factor given Induced Drag Coefficient?

The Induced drag factor given induced drag coefficient formula calculates induced drag factor which is a function of the Fourier series constants which has been used for the general circulation distribution expression for the finite wing and is represented as δ = (pi*AR_GLD*C_D,i,GLD)/C_L,GLD^2-1 or Induced Drag Factor = (pi*Wing Aspect Ratio GLD*Induced Drag Coefficient GLD)/Lift Coefficient GLD^2-1. 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, The Induced Drag Coefficient GLD is a dimensionless parameter that describes a relation between the coefficient of the lift and the aspect ratio & 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.

How to calculate Induced Drag Factor given Induced Drag Coefficient?

The Induced drag factor given induced drag coefficient formula calculates induced drag factor which is a function of the Fourier series constants which has been used for the general circulation distribution expression for the finite wing is calculated using Induced Drag Factor = (pi*Wing Aspect Ratio GLD*Induced Drag Coefficient GLD)/Lift Coefficient GLD^2-1. To calculate Induced Drag Factor given Induced Drag Coefficient, you need Wing Aspect Ratio GLD (AR_GLD), Induced Drag Coefficient GLD (C_D,i,GLD) & Lift Coefficient GLD (C_L,GLD). With our tool, you need to enter the respective value for Wing Aspect Ratio GLD, Induced Drag Coefficient GLD & Lift Coefficient 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 Factor?

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

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

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