FormulaDen.com

Physics Chemistry Math Chemical Engineering Civil Electrical Electronics Electronics and Instrumentation Materials Science Mechanical Production Engineering Financial Health

Lift Coefficient given Induced Drag Factor Formula

GoLift Coefficient given Span Efficiency Factor Formula

Fx Copy

LaTeX Copy

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. Check FAQs

C L,GLD = \sqrt{\frac{π \cdot AR GLD \cdot C D,i,GLD}{1 + δ}}

C_L,GLD - Lift Coefficient GLD?AR_GLD - Wing Aspect Ratio GLD?C_D,i,GLD - Induced Drag Coefficient GLD?δ - Induced Drag Factor?π - Archimedes' constant?

Lift Coefficient given Induced Drag Factor Example

With values

With units

Only example

Here is how the Lift Coefficient given Induced Drag Factor equation looks like with Values.

Here is how the Lift Coefficient given Induced Drag Factor equation looks like with Units.

Here is how the Lift Coefficient given Induced Drag Factor equation looks like.

1.4677 = \sqrt{\frac{3.1416 \cdot 15 \cdot 0.048}{1 + 0.05}}

1.4677 = \sqrt{\frac{3.1416 \cdot 15 \cdot 0.048}{1 + 0.05}}

1.4677 = \sqrt{\frac{3.1416 \cdot 15 \cdot 0.048}{1 + 0.05}}

Tip: Use pencil ( Pencil

) icon above to edit Input Values and Units.

Calculate

Recalculate

Solution

Copy

Reset

You are here -

Home » Category

Physics » Category

Aerospace » Category

Aerodynamics » fx Lift Coefficient given Induced Drag Factor

Lift Coefficient given Induced Drag Factor Solution

Follow our step by step solution on how to calculate Lift Coefficient given Induced Drag Factor?

FIRST Step Consider the formula

C L,GLD = \sqrt{\frac{π \cdot AR GLD \cdot C D,i,GLD}{1 + δ}}

Next Step Substitute values of Variables

∴

C L,GLD = \sqrt{\frac{π \cdot 15 \cdot 0.048}{1 + 0.05}}

Next Step Substitute values of Constants

∴

C L,GLD = \sqrt{\frac{3.1416 \cdot 15 \cdot 0.048}{1 + 0.05}}

Next Step Prepare to Evaluate

∴

C L,GLD = \sqrt{\frac{3.1416 \cdot 15 \cdot 0.048}{1 + 0.05}}

Next Step Evaluate

∴

C L,GLD = 1.46773122964035

LAST Step Rounding Answer

∴

C L,GLD = 1.4677

Lift Coefficient given Induced Drag Factor Formula Elements

Variables

Constants

Functions

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.

Symbol: C_L,GLD

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Lift Coefficient GLD

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.

Symbol: AR_GLD

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Wing Aspect Ratio GLD

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.

Symbol: C_D,i,GLD

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Induced Drag Coefficient GLD

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.

Symbol: δ

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Induced Drag Factor

Archimedes' constant

Archimedes' constant is a mathematical constant that represents the ratio of the circumference of a circle to its diameter.

Symbol: π

Value: 3.14159265358979323846264338327950288

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.

Syntax: sqrt(Number)

Other Formulas to find Lift Coefficient GLD

Go Lift Coefficient given Span Efficiency Factor

C L,GLD = \sqrt{π \cdot e span \cdot AR GLD \cdot C D,i,GLD}

Other formulas in General Lift Distribution category

Go Span Efficiency Factor

e span = {(1 + δ)}^{- 1}

Go Induced Drag Factor given Span Efficiency Factor

δ = {e span}^{- 1} - 1

Go Induced Drag Coefficient given Span Efficiency Factor

C D,i,GLD = \frac{{C L,GLD}^{2}}{π \cdot e span \cdot AR GLD}

Go Induced Lift Slope Factor given Lift Curve Slope of Finite Wing

τ FW = \frac{π \cdot AR GLD \cdot (\frac{a 0}{a C,l} - 1)}{a 0} - 1

How to Evaluate Lift Coefficient given Induced Drag Factor?

Lift Coefficient given Induced Drag Factor evaluator uses Lift Coefficient GLD = sqrt((pi*Wing Aspect Ratio GLD*Induced Drag Coefficient GLD)/(1+Induced Drag Factor)) to evaluate 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 evaluate Lift Coefficient given Induced Drag Factor using this online evaluator? To use this online evaluator 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.

FAQs on Lift Coefficient given Induced Drag Factor

What is the formula to find Lift Coefficient given Induced Drag Factor?

The formula of Lift Coefficient given Induced Drag Factor is expressed as Lift Coefficient GLD = sqrt((pi*Wing Aspect Ratio GLD*Induced Drag Coefficient GLD)/(1+Induced Drag Factor)). Here is an example- 1.339849 = sqrt((pi*15*0.048)/(1+0.05)).

How to calculate Lift Coefficient given Induced Drag Factor?

With Wing Aspect Ratio GLD (AR_GLD), Induced Drag Coefficient GLD (C_D,i,GLD) & Induced Drag Factor (δ) we can find Lift Coefficient given Induced Drag Factor using the formula - Lift Coefficient GLD = sqrt((pi*Wing Aspect Ratio GLD*Induced Drag Coefficient GLD)/(1+Induced Drag Factor)). This formula also uses Archimedes' constant and Square Root (sqrt) function(s).

What are the other ways to Calculate Lift Coefficient GLD?

Here are the different ways to Calculate Lift Coefficient GLD-

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

Let Others Know

✖

Facebook

Twitter

Copied!

: Value
: Unit

Lift Coefficient given Induced Drag Factor Formula

​GoLift Coefficient given Span Efficiency Factor Formula

Lift Coefficient given Induced Drag Factor Example

Lift Coefficient given Induced Drag Factor Solution

Lift Coefficient given Induced Drag Factor Formula Elements

Other Formulas to find Lift Coefficient GLD

Other formulas in General Lift Distribution category

How to Evaluate Lift Coefficient given Induced Drag Factor?

FAQs on Lift Coefficient given Induced Drag Factor

Variable Name

GoLift Coefficient given Span Efficiency Factor Formula