Coefficient of Lift for Airfoil Calculator

✖Angle of attack on airfoil is the angle between a reference line on airfoil and the vector representing the relative motion between the airfoil and the fluid through which it is moving.ⓘ Angle of Attack on Airfoil [α]

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✖Lift coefficient for airfoil is a 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.ⓘ Coefficient of Lift for Airfoil [C_{L airfoil}]

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Formula

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Coefficient of Lift for Airfoil

Formula

`"C"_{"L airfoil"} = 2*pi*sin("α")`

Example

`"0.711277"=2*pi*sin("6.5°")`

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Coefficient of Lift for Airfoil Solution

STEP 0: Pre-Calculation Summary

Formula Used

Lift Coefficient for Airfoil = 2*pi*sin(Angle of Attack on Airfoil)
C_{L airfoil} = 2*pi*sin(α)
This formula uses 1 Constants, 1 Functions, 2 Variables

Constants Used

pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288

Functions Used

sin - Sine is a trigonometric function that describes the ratio of the length of the opposite side of a right triangle to the length of the hypotenuse., sin(Angle)

Variables Used

Lift Coefficient for Airfoil - Lift coefficient for airfoil is a 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.
Angle of Attack on Airfoil - (Measured in Radian) - Angle of attack on airfoil is the angle between a reference line on airfoil and the vector representing the relative motion between the airfoil and the fluid through which it is moving.

STEP 1: Convert Input(s) to Base Unit

Angle of Attack on Airfoil: 6.5 Degree --> 0.11344640137961 Radian (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_{L airfoil} = 2*pi*sin(α) --> 2*pi*sin(0.11344640137961)

Evaluating ... ...

C_{L airfoil} = 0.711276769471888

STEP 3: Convert Result to Output's Unit

0.711276769471888 --> No Conversion Required

FINAL ANSWER

0.711276769471888 ≈ 0.711277 <-- Lift Coefficient for Airfoil

(Calculation completed in 00.004 seconds)

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Home » Physics » Fluid Mechanics » Fluid Statistics » Forces on Submerged Bodies » Lift and Circulation » Coefficient of Lift for Airfoil

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< 16 Lift and Circulation Calculators

Lift Force for Body moving in Fluid

Go Lift Force on Body in Fluid = (Lift Coefficient for Body in Fluid*Projected Area of Body*Mass of Flowing Fluid*(Velocity of Body or Fluid^2))/(Volume of Flowing Fluid*2)

Circulation in Location of Stagnation Points

Go Circulation Around Cylinder = -(sin(Angle at Stagnation Point))*4*pi*Freestream Velocity of Fluid*Radius of Rotating Cylinder

Lift coefficient for lift force in body moving on fluid

Go Lift Coefficient for Body in Fluid = Lift Force on Body in Fluid/(Projected Area of Body*0.5*Density of Fluid Circulating*(Velocity of Body or Fluid^2))

Lift Force for body moving in Fluid of Certain Density

Go Lift Force on Rotating Cylinder = Lift Coefficient for Body in Fluid*Projected Area of Body*Density of Fluid Circulating*(Velocity of Body or Fluid^2)/2

Lift Force on Cylinder for Circulation

Go Lift Force on Rotating Cylinder = Density of Fluid Circulating*Length of Cylinder in Fluid Flow*Circulation Around Cylinder*Freestream Velocity of Fluid

Angle of Attack for Circulation developed on Airfoil

Go Angle of Attack on Airfoil = asin(Circulation on Airfoil/(pi*Velocity of Airfoil*Chord Length of Airfoil))

Velocity of Airfoil for Circulation developed on Airfoil

Go Velocity of Airfoil = Circulation on Airfoil/(pi*Chord Length of Airfoil*sin(Angle of Attack on Airfoil))

Chord Length for Circulation developed on Airfoil

Go Chord Length of Airfoil = Circulation on Airfoil/(pi*Velocity of Airfoil*sin(Angle of Attack on Airfoil))

Circulation developed on Airfoil

Go Circulation on Airfoil = pi*Velocity of Airfoil*Chord Length of Airfoil*sin(Angle of Attack on Airfoil)

Radius of Cylinder for Lift Coefficient in Rotating Cylinder with Circulation

Go Radius of Rotating Cylinder = Circulation Around Cylinder/(Lift Coefficient for Rotating Cylinder*Freestream Velocity of Fluid)

Lift Coefficient for Rotating Cylinder with Circulation

Go Lift Coefficient for Rotating Cylinder = Circulation Around Cylinder/(Radius of Rotating Cylinder*Freestream Velocity of Fluid)

Tangential Velocity of Cylinder with Lift Coefficient

Go Tangential Velocity of Cylinder in Fluid = (Lift Coefficient for Rotating Cylinder*Freestream Velocity of Fluid)/(2*pi)

Lift Coefficient for Rotating Cylinder with Tangential Speed

Go Lift Coefficient for Rotating Cylinder = (2*pi*Tangential Velocity of Cylinder in Fluid)/Freestream Velocity of Fluid

Circulation for Single Stagnation Point

Go Circulation Around Cylinder = 4*pi*Freestream Velocity of Fluid*Radius of Rotating Cylinder

Angle of Attack for Lift Coefficient on Airfoil

Go Angle of Attack on Airfoil = asin(Lift Coefficient for Airfoil/(2*pi))

Coefficient of Lift for Airfoil

Go Lift Coefficient for Airfoil = 2*pi*sin(Angle of Attack on Airfoil)

Coefficient of Lift for Airfoil Formula

Lift Coefficient for Airfoil = 2*pi*sin(Angle of Attack on Airfoil)
C_{L airfoil} = 2*pi*sin(α)

What is a good coefficient of lift?

A typical value for the type of airfoil section mentioned is about 1.5. The corresponding value is around 18 degrees.

How to increase the coefficient of lift?

A leading-edge flap increases the curvature of the top of the airfoil. This considerably increases the lift coefficient. A movable slat (slotted leading-edge flap) increases the lift through a combination of increased wing area and increased camber and through the influence of the flow with the aid of the slat.

How to Calculate Coefficient of Lift for Airfoil?

Coefficient of Lift for Airfoil calculator uses Lift Coefficient for Airfoil = 2*pi*sin(Angle of Attack on Airfoil) to calculate the Lift Coefficient for Airfoil, The Coefficient of lift for airfoil formula is known while considering the value of two pi and sin with an angle. This angle is considered as the angle of attack. Lift Coefficient for Airfoil is denoted by C_{L airfoil} symbol.

How to calculate Coefficient of Lift for Airfoil using this online calculator? To use this online calculator for Coefficient of Lift for Airfoil, enter Angle of Attack on Airfoil (α) and hit the calculate button. Here is how the Coefficient of Lift for Airfoil calculation can be explained with given input values -> 0.711277 = 2*pi*sin(0.11344640137961).

FAQ

What is Coefficient of Lift for Airfoil?

The Coefficient of lift for airfoil formula is known while considering the value of two pi and sin with an angle. This angle is considered as the angle of attack and is represented as C_{L airfoil} = 2*pi*sin(α) or Lift Coefficient for Airfoil = 2*pi*sin(Angle of Attack on Airfoil). Angle of attack on airfoil is the angle between a reference line on airfoil and the vector representing the relative motion between the airfoil and the fluid through which it is moving.

How to calculate Coefficient of Lift for Airfoil?

The Coefficient of lift for airfoil formula is known while considering the value of two pi and sin with an angle. This angle is considered as the angle of attack is calculated using Lift Coefficient for Airfoil = 2*pi*sin(Angle of Attack on Airfoil). To calculate Coefficient of Lift for Airfoil, you need Angle of Attack on Airfoil (α). With our tool, you need to enter the respective value for Angle of Attack on Airfoil and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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