Angle of Attack for Lift Coefficient on Airfoil Calculator

✖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.ⓘ Lift Coefficient for Airfoil [C_{L airfoil}]

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✖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 for Lift Coefficient on Airfoil [α]

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Angle of Attack for Lift Coefficient on Airfoil Solution

STEP 0: Pre-Calculation Summary

Formula Used

Angle of Attack on Airfoil = asin(Lift Coefficient for Airfoil/(2*pi))
α = asin(C_{L airfoil}/(2*pi))
This formula uses 1 Constants, 2 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)
asin - The inverse sine function, is a trigonometric function that takes a ratio of two sides of a right triangle and outputs the angle opposite the side with the given ratio., asin(Number)

Variables Used

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.
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.

STEP 1: Convert Input(s) to Base Unit

Lift Coefficient for Airfoil: 0.712 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

α = asin(C_{L airfoil}/(2*pi)) --> asin(0.712/(2*pi))

Evaluating ... ...

α = 0.113562252561205

STEP 3: Convert Result to Output's Unit

0.113562252561205 Radian -->6.506637783757 Degree (Check conversion here)

FINAL ANSWER

6.506637783757 ≈ 6.506638 Degree <-- Angle of Attack on Airfoil

(Calculation completed in 00.004 seconds)

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

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< 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)

Angle of Attack for Lift Coefficient on Airfoil Formula

LaTeX Go

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

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 Angle of Attack for Lift Coefficient on Airfoil?

Angle of Attack for Lift Coefficient on Airfoil calculator uses Angle of Attack on Airfoil = asin(Lift Coefficient for Airfoil/(2*pi)) to calculate the Angle of Attack on Airfoil, The Angle of attack for lift coefficient on airfoil formula is known while considering the sin inverse with the ratio of lift coefficient to a constant value of two pi. Angle of Attack on Airfoil is denoted by α symbol.

How to calculate Angle of Attack for Lift Coefficient on Airfoil using this online calculator? To use this online calculator for Angle of Attack for Lift Coefficient on Airfoil, enter Lift Coefficient for Airfoil (C_{L airfoil}) and hit the calculate button. Here is how the Angle of Attack for Lift Coefficient on Airfoil calculation can be explained with given input values -> 372.8029 = asin(0.712/(2*pi)).

FAQ

What is Angle of Attack for Lift Coefficient on Airfoil?

The Angle of attack for lift coefficient on airfoil formula is known while considering the sin inverse with the ratio of lift coefficient to a constant value of two pi and is represented as α = asin(C_{L airfoil}/(2*pi)) or Angle of Attack on Airfoil = asin(Lift Coefficient for Airfoil/(2*pi)). 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.

How to calculate Angle of Attack for Lift Coefficient on Airfoil?

The Angle of attack for lift coefficient on airfoil formula is known while considering the sin inverse with the ratio of lift coefficient to a constant value of two pi is calculated using Angle of Attack on Airfoil = asin(Lift Coefficient for Airfoil/(2*pi)). To calculate Angle of Attack for Lift Coefficient on Airfoil, you need Lift Coefficient for Airfoil (C_{L airfoil}). With our tool, you need to enter the respective value for Lift Coefficient for Airfoil and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Angle of Attack on Airfoil?

In this formula, Angle of Attack on Airfoil uses Lift Coefficient for Airfoil. We can use 1 other way(s) to calculate the same, which is/are as follows -

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

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