Velocity of Airfoil for Circulation developed on Airfoil Solution

STEP 0: Pre-Calculation Summary
Formula Used
Velocity of Airfoil = Circulation on Airfoil/(pi*Chord Length of Airfoil*sin(Angle of Attack on Airfoil))
U = Γ/(pi*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
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.
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.
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 aerfoil.
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
Circulation on Airfoil: 62 Square Meter per Second --> 62 Square 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
U = Γ/(pi*C*sin(α)) --> 62/(pi*2.15*sin(0.11344640137961))
Evaluating ... ...
U = 81.0857616613482
STEP 3: Convert Result to Output's Unit
81.0857616613482 Meter per Second --> No Conversion Required
FINAL ANSWER
81.0857616613482 81.08576 Meter per Second <-- Velocity of Airfoil
(Calculation completed in 00.020 seconds)

Credits

Created by Maiarutselvan V
PSG College of Technology (PSGCT), Coimbatore
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Indian Institute of Technology (IIT), Bombay
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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)

Velocity of Airfoil for Circulation developed on Airfoil Formula

Velocity of Airfoil = Circulation on Airfoil/(pi*Chord Length of Airfoil*sin(Angle of Attack on Airfoil))
U = Γ/(pi*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 Velocity of Airfoil for Circulation developed on Airfoil?

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

How to calculate Velocity of Airfoil for Circulation developed on Airfoil using this online calculator? To use this online calculator for Velocity of Airfoil for Circulation developed on Airfoil, enter Circulation on Airfoil (Γ), Chord Length of Airfoil (C) & Angle of Attack on Airfoil (α) and hit the calculate button. Here is how the Velocity of Airfoil for Circulation developed on Airfoil calculation can be explained with given input values -> 81.08576 = 62/(pi*2.15*sin(0.11344640137961)).

FAQ

What is Velocity of Airfoil for Circulation developed on Airfoil?
The Velocity of airfoil for circulation developed on airfoil formula is known while considering the ratio of circulation to the chord length, and the angle of attack and is represented as U = Γ/(pi*C*sin(α)) or Velocity of Airfoil = Circulation on Airfoil/(pi*Chord Length of Airfoil*sin(Angle of Attack on Airfoil)). 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, Chord length of airfoil is an imaginary straight line joining the leading edge and trailing edge of an aerfoil & 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 Velocity of Airfoil for Circulation developed on Airfoil?
The Velocity of airfoil for circulation developed on airfoil formula is known while considering the ratio of circulation to the chord length, and the angle of attack is calculated using Velocity of Airfoil = Circulation on Airfoil/(pi*Chord Length of Airfoil*sin(Angle of Attack on Airfoil)). To calculate Velocity of Airfoil for Circulation developed on Airfoil, you need Circulation on Airfoil (Γ), Chord Length of Airfoil (C) & Angle of Attack on Airfoil (α). With our tool, you need to enter the respective value for Circulation on 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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