Coefficient of Lift for Airfoil Calculator

✖Angle of Attack on Airfoil is the angle between a reference line on an 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]

+10%

-10%

✖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}]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Lift and Circulation Formulas PDF PDF Image

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 an 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)

You are here -

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

Credits

Created by Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

Maiarutselvan V has created this Calculator and 300+ more calculators!

Verified by Sai Venkata Phanindra Chary Arendra

Vallurupalli Nageswara Rao Vignana Jyothi Institute of Engineering and Technology (VNRVJIET), Hyderabad

Sai Venkata Phanindra Chary Arendra has verified this Calculator and 300+ more calculators!

< Lift and Circulation Calculators

Angle of Attack for Circulation developed on Airfoil

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

Chord Length for Circulation developed on Airfoil

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

Circulation developed on Airfoil

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

Coefficient of Lift for Airfoil

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

Coefficient of Lift for Airfoil Formula

LaTeX Go

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 defined as 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 and is calculated 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 defined as 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 and is calculated 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 an 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 defined as 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 and is calculated 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.

Home

FREE PDFs

🔍 Search