Moment Coefficient about Leading-Edge for Symmetrical Airfoil by Thin Airfoil Theory Solution

STEP 0: Pre-Calculation Summary
Formula Used
Moment Coefficient about Leading Edge = -Lift Coefficient/4
Cm,le = -CL/4
This formula uses 2 Variables
Variables Used
Moment Coefficient about Leading Edge - Moment Coefficient about Leading Edge is obtained by dividing the moment about the leading edge by the dynamic pressure, the area, and the chord of the airfoil.
Lift Coefficient - The Lift Coefficient is a dimensionless 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: 1.2 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
Cm,le = -CL/4 --> -1.2/4
Evaluating ... ...
Cm,le = -0.3
STEP 3: Convert Result to Output's Unit
-0.3 --> No Conversion Required
FINAL ANSWER
-0.3 <-- Moment Coefficient about Leading Edge
(Calculation completed in 00.004 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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8 Flow over Airfoils Calculators

Boundary Layer Thickness for Laminar Flow
Go Laminar Boundary Layer Thickness = 5*Distance on X-Axis/sqrt(Reynolds Number for Laminar Flow)
Center of Pressure Location for Cambered Airfoil
Go Center of Pressure = -(Moment Coefficient about Leading Edge*Chord)/Lift Coefficient
Lift Coefficient for Cambered Airfoil
Go Lift Coefficient for Cambered Airfoil = 2*pi*(Angle of Attack-Angle of Zero Lift)
Boundary Layer Thickness for Turbulent Flow
Go Turbulent Boundary Layer Thickness = 0.37*Distance on X-Axis/(Reynolds Number for Turbulent Flow^(1/5))
Skin Friction Drag Coefficient for Flat Plate in Laminar Flow
Go Skin Friction Drag Coefficient = 1.328/(sqrt(Reynolds Number for Laminar Flow))
Skin Friction Drag Coefficient for Flat Plate in Turbulent Flow
Go Skin Friction Drag Coefficient = 0.074/(Reynolds Number for Turbulent Flow^(1/5))
Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory
Go Lift Coefficient = 2*pi*Angle of Attack
Moment Coefficient about Leading-Edge for Symmetrical Airfoil by Thin Airfoil Theory
Go Moment Coefficient about Leading Edge = -Lift Coefficient/4

Moment Coefficient about Leading-Edge for Symmetrical Airfoil by Thin Airfoil Theory Formula

Moment Coefficient about Leading Edge = -Lift Coefficient/4
Cm,le = -CL/4

What is the thin airfoil theory?

Thin airfoil theory is predicated on the replacement of the airfoil by the mean camber line. A vortex sheet is placed along the chord line, and its strength adjusted such that, in conjunction with the uniform freestream, the camber line becomes a streamline of the flow while at the same time satisfying the Kutta condition.

How to Calculate Moment Coefficient about Leading-Edge for Symmetrical Airfoil by Thin Airfoil Theory?

Moment Coefficient about Leading-Edge for Symmetrical Airfoil by Thin Airfoil Theory calculator uses Moment Coefficient about Leading Edge = -Lift Coefficient/4 to calculate the Moment Coefficient about Leading Edge, The Moment coefficient about leading-edge for symmetrical airfoil by Thin airfoil theory formula is obtained as the one-fourth of the lift coefficient. Moment Coefficient about Leading Edge is denoted by Cm,le symbol.

How to calculate Moment Coefficient about Leading-Edge for Symmetrical Airfoil by Thin Airfoil Theory using this online calculator? To use this online calculator for Moment Coefficient about Leading-Edge for Symmetrical Airfoil by Thin Airfoil Theory, enter Lift Coefficient (CL) and hit the calculate button. Here is how the Moment Coefficient about Leading-Edge for Symmetrical Airfoil by Thin Airfoil Theory calculation can be explained with given input values -> -0.3 = -1.2/4.

FAQ

What is Moment Coefficient about Leading-Edge for Symmetrical Airfoil by Thin Airfoil Theory?
The Moment coefficient about leading-edge for symmetrical airfoil by Thin airfoil theory formula is obtained as the one-fourth of the lift coefficient and is represented as Cm,le = -CL/4 or Moment Coefficient about Leading Edge = -Lift Coefficient/4. The Lift Coefficient is a dimensionless 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 Moment Coefficient about Leading-Edge for Symmetrical Airfoil by Thin Airfoil Theory?
The Moment coefficient about leading-edge for symmetrical airfoil by Thin airfoil theory formula is obtained as the one-fourth of the lift coefficient is calculated using Moment Coefficient about Leading Edge = -Lift Coefficient/4. To calculate Moment Coefficient about Leading-Edge for Symmetrical Airfoil by Thin Airfoil Theory, you need Lift Coefficient (CL). With our tool, you need to enter the respective value for Lift Coefficient 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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