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Maximum Lift coefficient for given liftoff velocity Formula

GoMaximum Lift coefficient for given stall velocity Formula

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Maximum Lift Coefficient is defined as the lift coefficient of the airfoil at stalling angle of attack. Check FAQs

C L,max = 2.88 \cdot \frac{W}{ρ ∞ \cdot S \cdot ({V LO}^{2})}

C_L,max - Maximum Lift Coefficient?W - Weight?ρ_∞ - Freestream Density?S - Reference Area?V_LO - Liftoff velocity?

Maximum Lift coefficient for given liftoff velocity Example

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Here is how the Maximum Lift coefficient for given liftoff velocity equation looks like with Values.

Here is how the Maximum Lift coefficient for given liftoff velocity equation looks like with Units.

Here is how the Maximum Lift coefficient for given liftoff velocity equation looks like.

0.0009 = 2.88 \cdot \frac{60.5}{1.225 \cdot 5.08 \cdot ({177.6}^{2})}

0.0009 = 2.88 \cdot \frac{60.5N}{1.225kg/m³ \cdot 5.08m² \cdot ({177.6m/s}^{2})}

0.0009 = 2.88 \cdot \frac{60.5}{1.225 \cdot 5.08 \cdot ({177.6}^{2})}

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Maximum Lift coefficient for given liftoff velocity Solution

Follow our step by step solution on how to calculate Maximum Lift coefficient for given liftoff velocity?

FIRST Step Consider the formula

C L,max = 2.88 \cdot \frac{W}{ρ ∞ \cdot S \cdot ({V LO}^{2})}

Next Step Substitute values of Variables

∴

C L,max = 2.88 \cdot \frac{60.5N}{1.225kg/m³ \cdot 5.08m² \cdot ({177.6m/s}^{2})}

Next Step Prepare to Evaluate

∴

C L,max = 2.88 \cdot \frac{60.5}{1.225 \cdot 5.08 \cdot ({177.6}^{2})}

Next Step Evaluate

∴

C L,max = 0.000887691657764317

LAST Step Rounding Answer

∴

C L,max = 0.0009

Maximum Lift coefficient for given liftoff velocity Formula Elements

Variables

Maximum Lift Coefficient

Maximum Lift Coefficient is defined as the lift coefficient of the airfoil at stalling angle of attack.

Symbol: C_L,max

Measurement: NAUnit: Unitless

Note: Value should be greater than 0.

Formulas to find Maximum Lift Coefficient

Weight

Weight Newton is a vector quantity and defined as the product of mass and acceleration acting on that mass.

Symbol: W

Measurement: ForceUnit: N

Note: Value can be positive or negative.

Formulas to find Weight

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

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

Liftoff velocity

Liftoff velocity is defined as the velocity of the aircraft at which it first becomes airborne.

Symbol: V_LO

Measurement: SpeedUnit: m/s

Note: Value should be greater than 0.

Formulas to find Liftoff velocity

Other Formulas to find Maximum Lift Coefficient

Go Maximum Lift coefficient for given stall velocity

C L,max = 2 \cdot \frac{W}{ρ ∞ \cdot S \cdot ({V stall}^{2})}

Other formulas in Take Off category

Go Resistance force during ground roll

R = μ r \cdot (W - F L)

Go Coefficient of rolling friction during ground roll

μ r = \frac{R}{W - F L}

Go Weight of aircraft during ground roll

W = (\frac{R}{μ r}) + F L

Go Lift acting on aircraft during ground roll

F L = W - (\frac{R}{μ r})

How to Evaluate Maximum Lift coefficient for given liftoff velocity?

Maximum Lift coefficient for given liftoff velocity evaluator uses Maximum Lift Coefficient = 2.88*Weight/(Freestream Density*Reference Area*(Liftoff velocity^2)) to evaluate the Maximum Lift Coefficient, Maximum Lift Coefficient for Given Liftoff Velocity is a measure that represents the maximum lift force an aircraft can generate at a given liftoff velocity, influenced by its weight, free stream density, reference area, and velocity, providing a critical design parameter for aircraft performance optimization. Maximum Lift Coefficient is denoted by C_L,max symbol.

How to evaluate Maximum Lift coefficient for given liftoff velocity using this online evaluator? To use this online evaluator for Maximum Lift coefficient for given liftoff velocity, enter Weight (W), Freestream Density (ρ_∞), Reference Area (S) & Liftoff velocity (V_LO) and hit the calculate button.

FAQs on Maximum Lift coefficient for given liftoff velocity

What is the formula to find Maximum Lift coefficient for given liftoff velocity?

The formula of Maximum Lift coefficient for given liftoff velocity is expressed as Maximum Lift Coefficient = 2.88*Weight/(Freestream Density*Reference Area*(Liftoff velocity^2)). Here is an example- 0.000888 = 2.88*60.5/(1.225*5.08*(177.6^2)).

How to calculate Maximum Lift coefficient for given liftoff velocity?

With Weight (W), Freestream Density (ρ_∞), Reference Area (S) & Liftoff velocity (V_LO) we can find Maximum Lift coefficient for given liftoff velocity using the formula - Maximum Lift Coefficient = 2.88*Weight/(Freestream Density*Reference Area*(Liftoff velocity^2)).

What are the other ways to Calculate Maximum Lift Coefficient?

Here are the different ways to Calculate Maximum Lift Coefficient-

Maximum Lift Coefficient=2*Weight/(Freestream Density*Reference Area*(Stall Velocity^2))

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Maximum Lift coefficient for given liftoff velocity Formula

​GoMaximum Lift coefficient for given stall velocity Formula

Maximum Lift coefficient for given liftoff velocity Example

Maximum Lift coefficient for given liftoff velocity Solution

Maximum Lift coefficient for given liftoff velocity Formula Elements

Other Formulas to find Maximum Lift Coefficient

Other formulas in Take Off category

How to Evaluate Maximum Lift coefficient for given liftoff velocity?

FAQs on Maximum Lift coefficient for given liftoff velocity

Variable Name

GoMaximum Lift coefficient for given stall velocity Formula