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Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle 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 = \frac{L Aircraft}{0.5 \cdot ρ \cdot (V^{2}) \cdot S}

C_l - Lift Coefficient?L_Aircraft - Lifting Force of Aircraft?ρ - Density Altitude for flying?V - Vehicle Speed?S - Aircraft Gross Wing Area?

Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle Example

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Here is how the Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle equation looks like with Values.

Here is how the Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle equation looks like with Units.

Here is how the Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle equation looks like.

0.0011 = \frac{1072.39}{0.5 \cdot 1.21 \cdot (268^{2}) \cdot 23}

0.0011 = \frac{1072.39kN}{0.5 \cdot 1.21kg/m³ \cdot ({268km/h}^{2}) \cdot 23m²}

0.0011 = \frac{1072.39}{0.5 \cdot 1.21 \cdot (268^{2}) \cdot 23}

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Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle Solution

Follow our step by step solution on how to calculate Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle?

FIRST Step Consider the formula

C l = \frac{L Aircraft}{0.5 \cdot ρ \cdot (V^{2}) \cdot S}

Next Step Substitute values of Variables

∴

C l = \frac{1072.39kN}{0.5 \cdot 1.21kg/m³ \cdot ({268km/h}^{2}) \cdot 23m²}

Next Step Prepare to Evaluate

∴

C l = \frac{1072.39}{0.5 \cdot 1.21 \cdot (268^{2}) \cdot 23}

Next Step Evaluate

∴

C l = 0.00107300058025019

LAST Step Rounding Answer

∴

C l = 0.0011

Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle Formula Elements

Variables

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 can be positive or negative.

Formulas to find Lift Coefficient

Lifting Force of Aircraft

Lifting Force of Aircraft provided by the wing-body of the vehicle. Lift is defined as the component of the aerodynamic force that is perpendicular to the flow direction.

Symbol: L_Aircraft

Measurement: ForceUnit: kN

Note: Value can be positive or negative.

Formulas to find Lifting Force of Aircraft

Density Altitude for flying

Density Altitude for flying is a representation of the amount of mass of a substance, material or object in relation to the space it occupies at an altitude.

Symbol: ρ

Measurement: DensityUnit: kg/m³

Note: Value can be positive or negative.

Formulas to find Density Altitude for flying

Vehicle Speed

Vehicle Speed (True Air Speed) of an aircraft is the speed of aircraft relative to air mass through which it is flying. The true airspeed is important information for accurate navigation of aircraft.

Symbol: V

Measurement: SpeedUnit: km/h

Note: Value can be positive or negative.

Formulas to find Vehicle Speed

Aircraft Gross Wing Area

Aircraft Gross Wing Area calculated by looking at the wing from a top-down view and measuring the area of the wing.

Symbol: S

Measurement: AreaUnit: m²

Note: Value can be positive or negative.

Formulas to find Aircraft Gross Wing Area

Other formulas in Aircraft Runway Length Estimation category

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Go Payload carried when desired take-off weight is considered

PYL = D - OEW - FW

Go Operating Empty Weight when Desired Take-off Weight is considered

OEW = D - PYL - FW

Go Fuel Weight to be Carried given Desired Takeoff Weight

FW = D - PYL - OEW

How to Evaluate Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle?

Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle evaluator uses Lift Coefficient = Lifting Force of Aircraft/(0.5*Density Altitude for flying*(Vehicle Speed^2)*Aircraft Gross Wing Area) to evaluate the Lift Coefficient, Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle is a number that aerodynamicists use to model all of the complex dependencies of shape, inclination, and some flow conditions on lift. Lift Coefficient is denoted by C_l symbol.

How to evaluate Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle using this online evaluator? To use this online evaluator for Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle, enter Lifting Force of Aircraft (L_Aircraft), Density Altitude for flying (ρ), Vehicle Speed (V) & Aircraft Gross Wing Area (S) and hit the calculate button.

FAQs on Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle

What is the formula to find Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle?

The formula of Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle is expressed as Lift Coefficient = Lifting Force of Aircraft/(0.5*Density Altitude for flying*(Vehicle Speed^2)*Aircraft Gross Wing Area). Here is an example- 0.001073 = 1072390/(0.5*1.21*(74.4444444444444^2)*23).

How to calculate Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle?

With Lifting Force of Aircraft (L_Aircraft), Density Altitude for flying (ρ), Vehicle Speed (V) & Aircraft Gross Wing Area (S) we can find Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle using the formula - Lift Coefficient = Lifting Force of Aircraft/(0.5*Density Altitude for flying*(Vehicle Speed^2)*Aircraft Gross Wing Area).

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Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle Formula

Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle Example

Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle Solution

Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle Formula Elements

Other formulas in Aircraft Runway Length Estimation category

How to Evaluate Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle?

FAQs on Lift Coefficient for Lifting Force Provided by Wing Body of Vehicle

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