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Maximum Lift coefficient for given stall velocity Formula

GoMaximum Lift coefficient for given liftoff 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 \cdot \frac{W}{ρ ∞ \cdot S \cdot ({V stall}^{2})}

C_L,max - Maximum Lift Coefficient?W - Weight?ρ_∞ - Freestream Density?S - Reference Area?V_stall - Stall Velocity?

Maximum Lift coefficient for given stall velocity Example

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

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

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

0.0009 = 2 \cdot \frac{60.5}{1.225 \cdot 5.08 \cdot (148^{2})}

0.0009 = 2 \cdot \frac{60.5N}{1.225kg/m³ \cdot 5.08m² \cdot ({148m/s}^{2})}

0.0009 = 2 \cdot \frac{60.5}{1.225 \cdot 5.08 \cdot (148^{2})}

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Maximum Lift coefficient for given stall velocity Solution

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

FIRST Step Consider the formula

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

Next Step Substitute values of Variables

∴

C L,max = 2 \cdot \frac{60.5N}{1.225kg/m³ \cdot 5.08m² \cdot ({148m/s}^{2})}

Next Step Prepare to Evaluate

∴

C L,max = 2 \cdot \frac{60.5}{1.225 \cdot 5.08 \cdot (148^{2})}

Next Step Evaluate

∴

C L,max = 0.000887691657764318

LAST Step Rounding Answer

∴

C L,max = 0.0009

Maximum Lift coefficient for given stall 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

Stall Velocity

Stall Velocity is defined as the velocity of an airplane in steady flight at its maximum lift coefficient.

Symbol: V_stall

Measurement: SpeedUnit: m/s

Note: Value should be greater than 0.

Formulas to find Stall Velocity

Other Formulas to find Maximum Lift Coefficient

Go Maximum Lift coefficient for given liftoff velocity

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

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Go Resistance force during ground roll

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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 stall velocity?

Maximum Lift coefficient for given stall velocity evaluator uses Maximum Lift Coefficient = 2*Weight/(Freestream Density*Reference Area*(Stall Velocity^2)) to evaluate the Maximum Lift Coefficient, Maximum Lift Coefficient for Given Stall Velocity is a measure of the highest lift force an airfoil can produce at a specific velocity, calculated by considering the weight tolerance, free stream density, reference area, and stall velocity tolerance, providing a critical metric for aerospace engineers to optimize aircraft performance. Maximum Lift Coefficient is denoted by C_L,max symbol.

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

FAQs on Maximum Lift coefficient for given stall velocity

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

The formula of Maximum Lift coefficient for given stall velocity is expressed as Maximum Lift Coefficient = 2*Weight/(Freestream Density*Reference Area*(Stall Velocity^2)). Here is an example- 0.000888 = 2*60.5/(1.225*5.08*(148^2)).

How to calculate Maximum Lift coefficient for given stall velocity?

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

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Maximum Lift coefficient for given stall velocity Formula

​GoMaximum Lift coefficient for given liftoff velocity Formula

Maximum Lift coefficient for given stall velocity Example

Maximum Lift coefficient for given stall velocity Solution

Maximum Lift coefficient for given stall velocity Formula Elements

Other Formulas to find Maximum Lift Coefficient

Other formulas in Take Off category

How to Evaluate Maximum Lift coefficient for given stall velocity?

FAQs on Maximum Lift coefficient for given stall velocity

Variable Name

GoMaximum Lift coefficient for given liftoff velocity Formula