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Lift Coefficient given Minimum required Thrust Formula

GoCoefficient of Lift for given Thrust-to-Weight Ratio Formula

GoCoefficient of Lift for given thrust and weight Formula

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The Lift Coefficient 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 = \sqrt{π \cdot e \cdot AR \cdot ((\frac{T}{P dynamic \cdot A}) - C D,0)}

C_L - Lift Coefficient?e - Oswald Efficiency Factor?AR - Aspect Ratio of a Wing?T - Thrust?P_dynamic - Dynamic Pressure?A - Area?C_D,0 - Zero Lift Drag Coefficient?π - Archimedes' constant?

Lift Coefficient given Minimum required Thrust Example

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Here is how the Lift Coefficient given Minimum required Thrust equation looks like with Values.

Here is how the Lift Coefficient given Minimum required Thrust equation looks like with Units.

Here is how the Lift Coefficient given Minimum required Thrust equation looks like.

1.1035 = \sqrt{3.1416 \cdot 0.51 \cdot 4 \cdot ((\frac{100}{10 \cdot 20}) - 0.31)}

1.1035 = \sqrt{3.1416 \cdot 0.51 \cdot 4 \cdot ((\frac{100N}{10Pa \cdot 20m²}) - 0.31)}

1.1035 = \sqrt{3.1416 \cdot 0.51 \cdot 4 \cdot ((\frac{100}{10 \cdot 20}) - 0.31)}

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Lift Coefficient given Minimum required Thrust Solution

Follow our step by step solution on how to calculate Lift Coefficient given Minimum required Thrust?

FIRST Step Consider the formula

C L = \sqrt{π \cdot e \cdot AR \cdot ((\frac{T}{P dynamic \cdot A}) - C D,0)}

Next Step Substitute values of Variables

∴

C L = \sqrt{π \cdot 0.51 \cdot 4 \cdot ((\frac{100N}{10Pa \cdot 20m²}) - 0.31)}

Next Step Substitute values of Constants

∴

C L = \sqrt{3.1416 \cdot 0.51 \cdot 4 \cdot ((\frac{100N}{10Pa \cdot 20m²}) - 0.31)}

Next Step Prepare to Evaluate

∴

C L = \sqrt{3.1416 \cdot 0.51 \cdot 4 \cdot ((\frac{100}{10 \cdot 20}) - 0.31)}

Next Step Evaluate

∴

C L = 1.10348598202759

LAST Step Rounding Answer

∴

C L = 1.1035

Lift Coefficient given Minimum required Thrust Formula Elements

Variables

Constants

Functions

Lift Coefficient

The Lift Coefficient 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

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Lift Coefficient

Oswald Efficiency Factor

The Oswald Efficiency Factor is a correction factor that represents the change in drag with lift of a three-dimensional wing or airplane, as compared with an ideal wing having the same aspect ratio.

Symbol: e

Measurement: NAUnit: Unitless

Note: Value should be less than 1.

Formulas to find Oswald Efficiency Factor

Aspect Ratio of a Wing

The Aspect Ratio of a Wing is defined as the ratio of its span to its mean chord.

Symbol: AR

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Aspect Ratio of a Wing

Thrust

The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.

Symbol: T

Measurement: ForceUnit: N

Note: Value should be greater than 0.

Formulas to find Thrust

Dynamic Pressure

Dynamic Pressure is a measure of the kinetic energy per unit volume of a fluid in motion.

Symbol: P_dynamic

Measurement: PressureUnit: Pa

Note: Value should be greater than 0.

Formulas to find Dynamic Pressure

Area

The Area is the amount of two-dimensional space taken up by an object.

Symbol: A

Measurement: AreaUnit: m²

Note: Value should be greater than 0.

Formulas to find Area

Zero Lift Drag Coefficient

Zero Lift Drag Coefficient is the coefficient of drag for an aircraft or aerodynamic body when it is producing zero lift.

Symbol: C_D,0

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Zero Lift Drag Coefficient

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

Go Coefficient of Lift for given Thrust-to-Weight Ratio

C L = \frac{C D}{TW}

Go Coefficient of Lift for given thrust and weight

C L = W body \cdot \frac{C D}{T}

Other formulas in Lift and Drag Requirements category

Go Drag for Level and Unaccelerated Flight

F D = T \cdot \cos (σ T)

Go Lift for Unaccelerated Flight

F L = W body - T \cdot \sin (σ T)

How to Evaluate Lift Coefficient given Minimum required Thrust?

Lift Coefficient given Minimum required Thrust evaluator uses Lift Coefficient = sqrt(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing*((Thrust/(Dynamic Pressure*Area))-Zero Lift Drag Coefficient)) to evaluate the Lift Coefficient, The Lift Coefficient given Minimum required Thrust equation allows us to calculate the lift coefficient for a given minimum required thrust, assuming level flight conditions where lift equals weight and thrust equals drag. Lift Coefficient is denoted by C_L symbol.

How to evaluate Lift Coefficient given Minimum required Thrust using this online evaluator? To use this online evaluator for Lift Coefficient given Minimum required Thrust, enter Oswald Efficiency Factor (e), Aspect Ratio of a Wing (AR), Thrust (T), Dynamic Pressure (P_dynamic), Area (A) & Zero Lift Drag Coefficient (C_D,0) and hit the calculate button.

FAQs on Lift Coefficient given Minimum required Thrust

What is the formula to find Lift Coefficient given Minimum required Thrust?

The formula of Lift Coefficient given Minimum required Thrust is expressed as Lift Coefficient = sqrt(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing*((Thrust/(Dynamic Pressure*Area))-Zero Lift Drag Coefficient)). Here is an example- 1.414058 = sqrt(pi*0.51*4*((100/(10*20))-0.31)).

How to calculate Lift Coefficient given Minimum required Thrust?

With Oswald Efficiency Factor (e), Aspect Ratio of a Wing (AR), Thrust (T), Dynamic Pressure (P_dynamic), Area (A) & Zero Lift Drag Coefficient (C_D,0) we can find Lift Coefficient given Minimum required Thrust using the formula - Lift Coefficient = sqrt(pi*Oswald Efficiency Factor*Aspect Ratio of a Wing*((Thrust/(Dynamic Pressure*Area))-Zero Lift Drag Coefficient)). This formula also uses Archimedes' constant and Square Root (sqrt) function(s).

What are the other ways to Calculate Lift Coefficient?

Here are the different ways to Calculate Lift Coefficient-

Lift Coefficient=Drag Coefficient/Thrust-to-Weight Ratio
Lift Coefficient=Weight of Body*Drag Coefficient/Thrust

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: Unit

Lift Coefficient given Minimum required Thrust Formula

​GoCoefficient of Lift for given Thrust-to-Weight Ratio Formula

​GoCoefficient of Lift for given thrust and weight Formula

Lift Coefficient given Minimum required Thrust Example

Lift Coefficient given Minimum required Thrust Solution

Lift Coefficient given Minimum required Thrust Formula Elements

Other Formulas to find Lift Coefficient

Other formulas in Lift and Drag Requirements category

How to Evaluate Lift Coefficient given Minimum required Thrust?

FAQs on Lift Coefficient given Minimum required Thrust

Variable Name

GoCoefficient of Lift for given Thrust-to-Weight Ratio Formula

GoCoefficient of Lift for given thrust and weight Formula