Circulation developed on Airfoil Calculator

✖The Velocity of Airfoil is the air velocity of a stream located in the airfoil where the flow has to part near the leading edge.ⓘ Velocity of Airfoil [U]			+10% -10%
✖Chord Length of Airfoil is an imaginary straight line joining the leading edge and trailing edge of an airfoil.ⓘ Chord Length of Airfoil [C]			+10% -10%
✖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%

✖Circulation on Airfoil is a scalar integral quantity, and is a macroscopic measure of rotation for a finite area of the fluid around an airfoil.ⓘ Circulation developed on Airfoil [Γ]

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Circulation developed on Airfoil Solution

STEP 0: Pre-Calculation Summary

Formula Used

Circulation on Airfoil = pi*Velocity of Airfoil*Chord Length of Airfoil*sin(Angle of Attack on Airfoil)
Γ = pi*U*C*sin(α)
This formula uses 1 Constants, 1 Functions, 4 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

Circulation on Airfoil - (Measured in Square Meter per Second) - Circulation on Airfoil is a scalar integral quantity, and is a macroscopic measure of rotation for a finite area of the fluid around an airfoil.
Velocity of Airfoil - (Measured in Meter per Second) - The Velocity of Airfoil is the air velocity of a stream located in the airfoil where the flow has to part near the leading edge.
Chord Length of Airfoil - (Measured in Meter) - Chord Length of Airfoil is an imaginary straight line joining the leading edge and trailing edge of an airfoil.
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

Velocity of Airfoil: 81 Meter per Second --> 81 Meter per Second No Conversion Required
Chord Length of Airfoil: 2.15 Meter --> 2.15 Meter No Conversion Required
Angle of Attack on Airfoil: 6.5 Degree --> 0.11344640137961 Radian (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Γ = pi*U*C*sin(α) --> pi*81*2.15*sin(0.11344640137961)

Evaluating ... ...

Γ = 61.9344247017646

STEP 3: Convert Result to Output's Unit

61.9344247017646 Square Meter per Second --> No Conversion Required

FINAL ANSWER

61.9344247017646 ≈ 61.93442 Square Meter per Second <-- Circulation on Airfoil

(Calculation completed in 00.004 seconds)

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Created by Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

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Indian Institute of Technology (IIT), Bombay

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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)

Circulation developed on Airfoil Formula

LaTeX Go

Circulation on Airfoil = pi*Velocity of Airfoil*Chord Length of Airfoil*sin(Angle of Attack on Airfoil)
Γ = pi*U*C*sin(α)

What is a circulation?

In physics, circulation is the line integral of a vector field around a closed curve. In fluid dynamics, the field is the fluid velocity field. In electrodynamics, it can be the electric or the magnetic field.

What is an airfoil?

An airfoil or aerofoil is the cross-sectional shape of a wing, blade, or sail. An airfoil-shaped body moving through a fluid produces an aerodynamic force.

How to Calculate Circulation developed on Airfoil?

Circulation developed on Airfoil calculator uses Circulation on Airfoil = pi*Velocity of Airfoil*Chord Length of Airfoil*sin(Angle of Attack on Airfoil) to calculate the Circulation on Airfoil, The Circulation developed on airfoil formula is known while considering the terms velocity of the airfoil, chord length, and the angle of attack. Circulation on Airfoil is denoted by Γ symbol.

How to calculate Circulation developed on Airfoil using this online calculator? To use this online calculator for Circulation developed on Airfoil, enter Velocity of Airfoil (U), Chord Length of Airfoil (C) & Angle of Attack on Airfoil (α) and hit the calculate button. Here is how the Circulation developed on Airfoil calculation can be explained with given input values -> 61.93442 = pi*81*2.15*sin(0.11344640137961).

FAQ

What is Circulation developed on Airfoil?

The Circulation developed on airfoil formula is known while considering the terms velocity of the airfoil, chord length, and the angle of attack and is represented as Γ = pi*U*C*sin(α) or Circulation on Airfoil = pi*Velocity of Airfoil*Chord Length of Airfoil*sin(Angle of Attack on Airfoil). The Velocity of Airfoil is the air velocity of a stream located in the airfoil where the flow has to part near the leading edge, Chord Length of Airfoil is an imaginary straight line joining the leading edge and trailing edge of an 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 Circulation developed on Airfoil?

The Circulation developed on airfoil formula is known while considering the terms velocity of the airfoil, chord length, and the angle of attack is calculated using Circulation on Airfoil = pi*Velocity of Airfoil*Chord Length of Airfoil*sin(Angle of Attack on Airfoil). To calculate Circulation developed on Airfoil, you need Velocity of Airfoil (U), Chord Length of Airfoil (C) & Angle of Attack on Airfoil (α). With our tool, you need to enter the respective value for Velocity of Airfoil, Chord Length of Airfoil & 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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