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Lift Coefficient for given Turn Rate Formula

GoLift Coefficient for given Turn Radius Formula

GoLift Coefficient for given wing loading and turn radius 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 = 2 \cdot W \cdot \frac{ω^{2}}{{[g]}^{2} \cdot ρ ∞ \cdot n \cdot S}

C_L - Lift Coefficient?W - Aircraft Weight?ω - Turn Rate?ρ_∞ - Freestream Density?n - Load Factor?S - Reference Area?[g] - Gravitational acceleration on Earth?

Lift Coefficient for given Turn Rate Example

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Here is how the Lift Coefficient for given Turn Rate equation looks like with Values.

Here is how the Lift Coefficient for given Turn Rate equation looks like with Units.

Here is how the Lift Coefficient for given Turn Rate equation looks like.

0.002 = 2 \cdot 1800 \cdot \frac{{1.144}^{2}}{{9.8066}^{2} \cdot 1.225 \cdot 1.2 \cdot 5.08}

0.002 = 2 \cdot 1800N \cdot \frac{{1.144degree/s}^{2}}{{9.8066m/s²}^{2} \cdot 1.225kg/m³ \cdot 1.2 \cdot 5.08m²}

0.002 = 2 \cdot 1800 \cdot \frac{{1.144}^{2}}{{9.8066}^{2} \cdot 1.225 \cdot 1.2 \cdot 5.08}

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Lift Coefficient for given Turn Rate Solution

Follow our step by step solution on how to calculate Lift Coefficient for given Turn Rate?

FIRST Step Consider the formula

C L = 2 \cdot W \cdot \frac{ω^{2}}{{[g]}^{2} \cdot ρ ∞ \cdot n \cdot S}

Next Step Substitute values of Variables

∴

C L = 2 \cdot 1800N \cdot \frac{{1.144degree/s}^{2}}{{[g]}^{2} \cdot 1.225kg/m³ \cdot 1.2 \cdot 5.08m²}

Next Step Substitute values of Constants

∴

C L = 2 \cdot 1800N \cdot \frac{{1.144degree/s}^{2}}{{9.8066m/s²}^{2} \cdot 1.225kg/m³ \cdot 1.2 \cdot 5.08m²}

Next Step Convert Units

∴

C L = 2 \cdot 1800N \cdot \frac{{0.02rad/s}^{2}}{{9.8066m/s²}^{2} \cdot 1.225kg/m³ \cdot 1.2 \cdot 5.08m²}

Next Step Prepare to Evaluate

∴

C L = 2 \cdot 1800 \cdot \frac{{0.02}^{2}}{{9.8066}^{2} \cdot 1.225 \cdot 1.2 \cdot 5.08}

Next Step Evaluate

∴

C L = 0.00199842054871387

LAST Step Rounding Answer

∴

C L = 0.002

Lift Coefficient for given Turn Rate Formula Elements

Variables

Constants

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

Aircraft Weight

Aircraft Weight is the total aircraft weight at any moment during the flight or ground operation.

Symbol: W

Measurement: ForceUnit: N

Note: Value should be greater than 0.

Formulas to find Aircraft Weight

Turn Rate

Turn Rate is the rate at which an aircraft executes a turn expressed in degrees per second.

Symbol: ω

Measurement: Angular VelocityUnit: degree/s

Note: Value should be greater than 0.

Formulas to find Turn Rate

Freestream Density

Freestream Density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.

Symbol: ρ_∞

Measurement: DensityUnit: kg/m³

Note: Value can be positive or negative.

Formulas to find Freestream Density

Load Factor

Load Factor is the ratio of the aerodynamic force on the aircraft to the gross weight of the aircraft.

Symbol: n

Measurement: NAUnit: Unitless

Note: Value can be positive or negative.

Formulas to find Load Factor

Reference Area

The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.

Symbol: S

Measurement: AreaUnit: m²

Note: Value should be greater than 0.

Formulas to find Reference Area

Gravitational acceleration on Earth

Gravitational acceleration on Earth means that the velocity of an object in free fall will increase by 9.8 m/s2 every second.

Symbol: [g]

Value: 9.80665 m/s²

Other Formulas to find Lift Coefficient

Go Lift Coefficient for given Turn Radius

C L = \frac{W}{0.5 \cdot ρ ∞ \cdot S \cdot [g] \cdot R}

Go Lift Coefficient for given wing loading and turn radius

C L = 2 \cdot \frac{W S}{ρ ∞ \cdot R \cdot [g]}

Other formulas in High Load Factor Maneuver category

Go Turn radius for high load factor

R = \frac{v^{2}}{[g] \cdot n}

Go Velocity given Turn Radius for High Load Factor

v = \sqrt{R \cdot n \cdot [g]}

Go Load factor for given turn radius for high-performance fighter aircraft

n = \frac{v^{2}}{[g] \cdot R}

Go Turn Rate for High Load Factor

ω = [g] \cdot \frac{n}{v}

How to Evaluate Lift Coefficient for given Turn Rate?

Lift Coefficient for given Turn Rate evaluator uses Lift Coefficient = 2*Aircraft Weight*(Turn Rate^2)/([g]^2*Freestream Density*Load Factor*Reference Area) to evaluate the Lift Coefficient, The Lift Coefficient for given Turn Rate quantifies the lift produced by an airfoil or body during a specific turn. This formula reveals how factors like aircraft weight, freestream density, load factor, and reference area interact with the turn rate to determine the lift coefficient. Understanding this coefficient is pivotal for evaluating aircraft aerodynamics during maneuvers, guiding flight performance assessments and maneuver planning. Lift Coefficient is denoted by C_L symbol.

How to evaluate Lift Coefficient for given Turn Rate using this online evaluator? To use this online evaluator for Lift Coefficient for given Turn Rate, enter Aircraft Weight (W), Turn Rate (ω), Freestream Density (ρ_∞), Load Factor (n) & Reference Area (S) and hit the calculate button.

FAQs on Lift Coefficient for given Turn Rate

What is the formula to find Lift Coefficient for given Turn Rate?

The formula of Lift Coefficient for given Turn Rate is expressed as Lift Coefficient = 2*Aircraft Weight*(Turn Rate^2)/([g]^2*Freestream Density*Load Factor*Reference Area). Here is an example- 0.001998 = 2*1800*(0.0199665666428114^2)/([g]^2*1.225*1.2*5.08).

How to calculate Lift Coefficient for given Turn Rate?

With Aircraft Weight (W), Turn Rate (ω), Freestream Density (ρ_∞), Load Factor (n) & Reference Area (S) we can find Lift Coefficient for given Turn Rate using the formula - Lift Coefficient = 2*Aircraft Weight*(Turn Rate^2)/([g]^2*Freestream Density*Load Factor*Reference Area). This formula also uses Gravitational acceleration on Earth constant(s).

What are the other ways to Calculate Lift Coefficient?

Here are the different ways to Calculate Lift Coefficient-

Lift Coefficient=Aircraft Weight/(0.5*Freestream Density*Reference Area*[g]*Turn Radius)
Lift Coefficient=2*Wing Loading/(Freestream Density*Turn Radius*[g])

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: Value
: Unit

Lift Coefficient for given Turn Rate Formula

​GoLift Coefficient for given Turn Radius Formula

​GoLift Coefficient for given wing loading and turn radius Formula

Lift Coefficient for given Turn Rate Example

Lift Coefficient for given Turn Rate Solution

Lift Coefficient for given Turn Rate Formula Elements

Other Formulas to find Lift Coefficient

Other formulas in High Load Factor Maneuver category

How to Evaluate Lift Coefficient for given Turn Rate?

FAQs on Lift Coefficient for given Turn Rate

Variable Name

GoLift Coefficient for given Turn Radius Formula

GoLift Coefficient for given wing loading and turn radius Formula