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

✖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.ⓘ Lift Coefficient [C_L]

+10%

-10%

✖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.ⓘ Moment Coefficient about Leading-Edge for Symmetrical Airfoil by Thin Airfoil Theory [C_m,le]

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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
C_m,le = -C_L/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

C_m,le = -C_L/4 --> -1.2/4

Evaluating ... ...

C_m,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)

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Created by Shikha Maurya

Indian Institute of Technology (IIT), Bombay

Shikha Maurya has created this Calculator and 100+ more calculators!

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PSG College of Technology (PSGCT), Coimbatore

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< Flow over Airfoils Calculators

Lift Coefficient for Cambered Airfoil

LaTeX Go Lift Coefficient for Cambered Airfoil = 2*pi*((Angle of Attack)-(Angle of Zero Lift))

Center of Pressure Location for Cambered Airfoil

LaTeX Go Center of Pressure = -(Moment Coefficient about Leading Edge*Chord)/Lift Coefficient

Lift Coefficient for Symmetrical Airfoil by Thin Airfoil Theory

LaTeX Go Lift Coefficient = 2*pi*Angle of Attack

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

LaTeX Go Moment Coefficient about Leading Edge = -Lift Coefficient/4

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

LaTeX Go

Moment Coefficient about Leading Edge = -Lift Coefficient/4
C_m,le = -C_L/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 This formula is derived from thin airfoil theory and represents the moment generated about the leading edge of a symmetrical airfoil due to the distribution of pressure over its surface. It assumes that the airfoil is thin enough such that the flow can be approximated as in viscid and that circulation around the airfoil can be represented by a constant vortex strength. Moment Coefficient about Leading Edge is denoted by C_m,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 (C_L) 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 This formula is derived from thin airfoil theory and represents the moment generated about the leading edge of a symmetrical airfoil due to the distribution of pressure over its surface. It assumes that the airfoil is thin enough such that the flow can be approximated as in viscid and that circulation around the airfoil can be represented by a constant vortex strength and is represented as C_m,le = -C_L/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 This formula is derived from thin airfoil theory and represents the moment generated about the leading edge of a symmetrical airfoil due to the distribution of pressure over its surface. It assumes that the airfoil is thin enough such that the flow can be approximated as in viscid and that circulation around the airfoil can be represented by a constant vortex strength 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 (C_L). 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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