Lift 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

✖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 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 given Induced Drag Factor [C_L,GLD]

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Formula

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Lift Coefficient given Induced Drag Factor

Formula

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

Example

`"1.467731"=sqrt((pi*"15"*"0.048")/(1+"0.05"))`

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Lift Coefficient given Induced Drag Factor Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

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 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.
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.

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
Induced Drag Factor: 0.05 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_L,GLD = sqrt((pi*AR_GLD*C_D,i,GLD)/(1+δ)) --> sqrt((pi*15*0.048)/(1+0.05))

Evaluating ... ...

C_L,GLD = 1.46773122964035

STEP 3: Convert Result to Output's Unit

1.46773122964035 --> No Conversion Required

FINAL ANSWER

1.46773122964035 ≈ 1.467731 <-- Lift Coefficient GLD

(Calculation completed in 00.020 seconds)

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< 10+ General Lift Distribution Calculators

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

Lift Coefficient given Induced Drag Factor Formula

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

Why does drag coefficient increase with lift coefficient?

At low angles, the drag is nearly constant. The effect is called induced drag or drag due to lift. The flow around the wingtips of a finite wing creates an "induced" angle of attack on the wing near the tips. As the angle increases, the lift coefficient increases and this changes the amount of the induced drag.

How to Calculate Lift Coefficient given Induced Drag Factor?

Lift Coefficient given Induced Drag Factor calculator uses Lift Coefficient GLD = sqrt((pi*Wing Aspect Ratio GLD*Induced Drag Coefficient GLD)/(1+Induced Drag Factor)) to calculate the Lift Coefficient GLD, The Lift coefficient given induced drag factor formula calculates the coefficient of lift which is an important parameter for the selection of the aerofoil and the aerodynamic efficiency of the wing. Lift Coefficient GLD is denoted by C_L,GLD symbol.

How to calculate Lift Coefficient given Induced Drag Factor using this online calculator? To use this online calculator for Lift Coefficient given Induced Drag Factor, enter Wing Aspect Ratio GLD (AR_GLD), Induced Drag Coefficient GLD (C_D,i,GLD) & Induced Drag Factor (δ) and hit the calculate button. Here is how the Lift Coefficient given Induced Drag Factor calculation can be explained with given input values -> 1.339849 = sqrt((pi*15*0.048)/(1+0.05)).

FAQ

What is Lift Coefficient given Induced Drag Factor?

The Lift coefficient given induced drag factor formula calculates the coefficient of lift which is an important parameter for the selection of the aerofoil and the aerodynamic efficiency of the wing and is represented as C_L,GLD = sqrt((pi*AR_GLD*C_D,i,GLD)/(1+δ)) or Lift Coefficient GLD = sqrt((pi*Wing Aspect Ratio GLD*Induced Drag Coefficient GLD)/(1+Induced Drag Factor)). 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 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.

How to calculate Lift Coefficient given Induced Drag Factor?

The Lift coefficient given induced drag factor formula calculates the coefficient of lift which is an important parameter for the selection of the aerofoil and the aerodynamic efficiency of the wing is calculated using Lift Coefficient GLD = sqrt((pi*Wing Aspect Ratio GLD*Induced Drag Coefficient GLD)/(1+Induced Drag Factor)). To calculate Lift Coefficient given Induced Drag Factor, you need Wing Aspect Ratio GLD (AR_GLD), Induced Drag Coefficient GLD (C_D,i,GLD) & Induced Drag Factor (δ). With our tool, you need to enter the respective value for Wing Aspect Ratio GLD, Induced Drag Coefficient GLD & Induced Drag Factor 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 Coefficient GLD?

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

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

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