2-D Lift Coefficient for Cylinder Solution

STEP 0: Pre-Calculation Summary
Formula Used
Lift Coefficient = Vortex Strength/(Cylinder Radius*Freestream Velocity)
CL = Γ/(R*V)
This formula uses 4 Variables
Variables Used
Lift Coefficient - Lift Coefficient is a dimensionless coefficient that relates the lift generated per unit span by a lifting body to the fluid density around the body, the fluid velocity & reference area.
Vortex Strength - (Measured in Square Meter per Second) - Vortex Strength quantifies the intensity or magnitude of a vortex in fluid dynamics.
Cylinder Radius - (Measured in Meter) - The Cylinder Radius is the radius of its circular cross section.
Freestream Velocity - (Measured in Meter per Second) - The Freestream Velocity signifies the speed or velocity of a fluid flow far from any disturbances or obstacles.
STEP 1: Convert Input(s) to Base Unit
Vortex Strength: 0.7 Square Meter per Second --> 0.7 Square Meter per Second No Conversion Required
Cylinder Radius: 0.08 Meter --> 0.08 Meter No Conversion Required
Freestream Velocity: 6.9 Meter per Second --> 6.9 Meter per Second No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
CL = Γ/(R*V) --> 0.7/(0.08*6.9)
Evaluating ... ...
CL = 1.26811594202899
STEP 3: Convert Result to Output's Unit
1.26811594202899 --> No Conversion Required
FINAL ANSWER
1.26811594202899 1.268116 <-- Lift Coefficient
(Calculation completed in 00.020 seconds)

Credits

Created by Shikha Maurya
Indian Institute of Technology (IIT), Bombay
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Verified by Maiarutselvan V
PSG College of Technology (PSGCT), Coimbatore
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10+ Lifting Flow over Cylinder Calculators

Surface Pressure Coefficient for Lifting Flow over Circular Cylinder
Go Surface Pressure Coefficient = 1-((2*sin(Polar Angle))^2+(2*Vortex Strength*sin(Polar Angle))/(pi*Cylinder Radius*Freestream Velocity)+((Vortex Strength)/(2*pi*Cylinder Radius*Freestream Velocity))^2)
Stream Function for Lifting Flow over Circular Cylinder
Go Stream Function = Freestream Velocity*Radial Coordinate*sin(Polar Angle)*(1-(Cylinder Radius/Radial Coordinate)^2)+Vortex Strength/(2*pi)*ln(Radial Coordinate/Cylinder Radius)
Location of Stagnation Point Outside Cylinder for Lifting Flow
Go Radial Coordinate of Stagnation Point = Stagnation Vortex Strength/(4*pi*Freestream Velocity)+sqrt((Stagnation Vortex Strength/(4*pi*Freestream Velocity))^2-Cylinder Radius^2)
Tangential Velocity for Lifting Flow over Circular Cylinder
Go Tangential Velocity = -(1+((Cylinder Radius)/(Radial Coordinate))^2)*Freestream Velocity*sin(Polar Angle)-(Vortex Strength)/(2*pi*Radial Coordinate)
Angular Position of Stagnation Point for Lifting Flow over Circular Cylinder
Go Polar Angle of Stagnation Point = arsin(-Stagnation Vortex Strength/(4*pi*Stagnation Freestream Velocity*Cylinder Radius))
Angular Position given Radial Velocity for Lifting Flow over Circular Cylinder
Go Polar Angle = arccos(Radial Velocity/((1-(Cylinder Radius/Radial Coordinate)^2)*Freestream Velocity))
Radial Velocity for Lifting Flow over Circular Cylinder
Go Radial Velocity = (1-(Cylinder Radius/Radial Coordinate)^2)*Freestream Velocity*cos(Polar Angle)
Freestream Velocity given 2-D Lift Coefficient for Lifting Flow
Go Freestream Velocity = Vortex Strength/(Cylinder Radius*Lift Coefficient)
Radius of Cylinder for Lifting Flow
Go Cylinder Radius = Vortex Strength/(Lift Coefficient*Freestream Velocity)
2-D Lift Coefficient for Cylinder
Go Lift Coefficient = Vortex Strength/(Cylinder Radius*Freestream Velocity)

2-D Lift Coefficient for Cylinder Formula

Lift Coefficient = Vortex Strength/(Cylinder Radius*Freestream Velocity)
CL = Γ/(R*V)

Can you compare lift and drag on the spinning cylinder and wing of same planform area?

The lift on the spinning cylinder is higher than an airplane wing of the same planform area however the drag on the spinning cylinder is also much higher than the well-designed wing.

How to Calculate 2-D Lift Coefficient for Cylinder?

2-D Lift Coefficient for Cylinder calculator uses Lift Coefficient = Vortex Strength/(Cylinder Radius*Freestream Velocity) to calculate the Lift Coefficient, The 2-D Lift coefficient for cylinder formula is defined as the function of the radius of the cylinder, freestream velocity and the strength of the vortex flow. Lift Coefficient is denoted by CL symbol.

How to calculate 2-D Lift Coefficient for Cylinder using this online calculator? To use this online calculator for 2-D Lift Coefficient for Cylinder, enter Vortex Strength (Γ), Cylinder Radius (R) & Freestream Velocity (V) and hit the calculate button. Here is how the 2-D Lift Coefficient for Cylinder calculation can be explained with given input values -> 23.55072 = 0.7/(0.08*6.9).

FAQ

What is 2-D Lift Coefficient for Cylinder?
The 2-D Lift coefficient for cylinder formula is defined as the function of the radius of the cylinder, freestream velocity and the strength of the vortex flow and is represented as CL = Γ/(R*V) or Lift Coefficient = Vortex Strength/(Cylinder Radius*Freestream Velocity). Vortex Strength quantifies the intensity or magnitude of a vortex in fluid dynamics, The Cylinder Radius is the radius of its circular cross section & The Freestream Velocity signifies the speed or velocity of a fluid flow far from any disturbances or obstacles.
How to calculate 2-D Lift Coefficient for Cylinder?
The 2-D Lift coefficient for cylinder formula is defined as the function of the radius of the cylinder, freestream velocity and the strength of the vortex flow is calculated using Lift Coefficient = Vortex Strength/(Cylinder Radius*Freestream Velocity). To calculate 2-D Lift Coefficient for Cylinder, you need Vortex Strength (Γ), Cylinder Radius (R) & Freestream Velocity (V). With our tool, you need to enter the respective value for Vortex Strength, Cylinder Radius & Freestream Velocity 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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