Moment Coefficient Calculator

✖Moment is an overturning effect (tends to bend or turn the member) created by the force(load) acting on a structural member.ⓘ Moment [M_t]			+10% -10%
✖Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.ⓘ Dynamic Pressure [q]			+10% -10%
✖Area for flow decreases velocity increases and vice versa. For subsonic flows, M < 1, the behavior resembles that for incompressible flows.ⓘ Area for Flow [A]			+10% -10%
✖Chord Length is the length of a line segment connecting any two points on the circumference of a circle.ⓘ Chord Length [L_c]			+10% -10%

✖The Moment Coefficient is divided by the dynamic pressure, the area and the chord of the airfoil, the result is known as the pitching moment coefficient.ⓘ Moment Coefficient [Cm]

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Formula

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Moment Coefficient

Formula

`"Cm" = "M"_{"t"}/("q"*"A"*"L"_{"c"})`

Example

`"0.031053"="59N*m"/("10Pa"*"50m²"*"3.8m")`

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Moment Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Moment Coefficient = Moment/(Dynamic Pressure*Area for Flow*Chord Length)
Cm = M_t/(q*A*L_c)
This formula uses 5 Variables

Variables Used

Moment Coefficient - The Moment Coefficient is divided by the dynamic pressure, the area and the chord of the airfoil, the result is known as the pitching moment coefficient.
Moment - (Measured in Joule) - Moment is an overturning effect (tends to bend or turn the member) created by the force(load) acting on a structural member.
Dynamic Pressure - (Measured in Pascal) - Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.
Area for Flow - (Measured in Square Meter) - Area for flow decreases velocity increases and vice versa. For subsonic flows, M < 1, the behavior resembles that for incompressible flows.
Chord Length - (Measured in Meter) - Chord Length is the length of a line segment connecting any two points on the circumference of a circle.

STEP 1: Convert Input(s) to Base Unit

Moment: 59 Newton Meter --> 59 Joule (Check conversion here)
Dynamic Pressure: 10 Pascal --> 10 Pascal No Conversion Required
Area for Flow: 50 Square Meter --> 50 Square Meter No Conversion Required
Chord Length: 3.8 Meter --> 3.8 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Cm = M_t/(q*A*L_c) --> 59/(10*50*3.8)

Evaluating ... ...

Cm = 0.0310526315789474

STEP 3: Convert Result to Output's Unit

0.0310526315789474 --> No Conversion Required

FINAL ANSWER

0.0310526315789474 ≈ 0.031053 <-- Moment Coefficient

(Calculation completed in 00.020 seconds)

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Created by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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K J Somaiya College of Engineering (K J Somaiya), Mumbai

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< 20 Hypersonic Flow Parameters Calculators

Coefficient of Pressure with Similarity Parameters

Go Pressure Coefficient = 2*Flow Deflection angle^2*((Specific Heat Ratio+1)/4+sqrt(((Specific Heat Ratio+1)/4)^2+1/Hypersonic Similarity Parameter^2))

Pressure Ratio having High Mach Number with Similarity Constant

Go Pressure Ratio = (1-((Specific Heat Ratio-1)/2)*Hypersonic Similarity Parameter)^(2*Specific Heat Ratio/(Specific Heat Ratio-1))

Mach Number with Fluids

Go Mach Number = Fluid Velocity/(sqrt(Specific Heat Ratio*Universal Gas Constant*Final Temperature))

Pressure Ratio for High Mach Number

Go Pressure Ratio = (Mach Number ahead of shock/Mach Number behind shock)^(2*Specific Heat Ratio/(Specific Heat Ratio-1))

Moment Coefficient

Go Moment Coefficient = Moment/(Dynamic Pressure*Area for Flow*Chord Length)

Deflection Angle

Go Deflection Angle = 2/(Specific Heat Ratio-1)*(1/Mach Number ahead of shock-1/Mach Number behind shock)

Normal Force Coefficient

Go Coefficient of Force = Normal Force/(Dynamic Pressure*Area for Flow)

Supersonic Expression for Pressure Coefficient on Surface with Local Deflection Angle

Go Pressure Coefficient = (2*Deflection Angle)/(sqrt(Mach Number^2-1))

Dynamic Pressure given Coefficient of Lift

Go Dynamic Pressure = Lift Force/(Lift Coefficient*Area for Flow)

Coefficient of Drag

Go Drag Coefficient = Drag Force/(Dynamic Pressure*Area for Flow)

Dynamic Pressure

Go Dynamic Pressure = Drag Force/(Drag Coefficient*Area for Flow)

Lift Coefficient

Go Lift Coefficient = Lift Force/(Dynamic Pressure*Area for Flow)

Axial Force Coefficient

Go Coefficient of Force = Force/(Dynamic Pressure*Area for Flow)

Drag Force

Go Drag Force = Drag Coefficient*Dynamic Pressure*Area for Flow

Lift Force

Go Lift Force = Lift Coefficient*Dynamic Pressure*Area for Flow

Mach Ratio at High Mach Number

Go Mach Ratio = 1-Hypersonic Similarity Parameter*((Specific Heat Ratio-1)/2)

Hypersonic Similarity Parameter

Go Hypersonic Similarity Parameter = Mach Number*Flow Deflection angle

Shear-Stress Distribution

Go Shear Stress = Viscosity Coefficient*Velocity Gradient

Fourier's Law of Heat Conduction

Go Heat Flux = Thermal Conductivity*Temperature Gradient

Newtonian Sine Squared Law for Pressure Coefficient

Go Pressure Coefficient = 2*sin(Deflection Angle)^2

Moment Coefficient Formula

Moment Coefficient = Moment/(Dynamic Pressure*Area for Flow*Chord Length)
Cm = M_t/(q*A*L_c)

What is coefficient of moment?

If the moment is divided by the dynamic pressure, the area and chord of the airfoil, the result is known as the pitching moment coefficient. This coefficient changes only a little over the operating range of angle of attack of the airfoil

How to Calculate Moment Coefficient?

Moment Coefficient calculator uses Moment Coefficient = Moment/(Dynamic Pressure*Area for Flow*Chord Length) to calculate the Moment Coefficient, The moment coefficient formula is defined as the ratio of moment M at any point on body due to hypersonic flow to the product of dynamic pressure, reference area and chord length. Moment Coefficient is denoted by Cm symbol.

How to calculate Moment Coefficient using this online calculator? To use this online calculator for Moment Coefficient, enter Moment (M_t), Dynamic Pressure (q), Area for Flow (A) & Chord Length (L_c) and hit the calculate button. Here is how the Moment Coefficient calculation can be explained with given input values -> 0.031053 = 59/(10*50*3.8).

FAQ

What is Moment Coefficient?

The moment coefficient formula is defined as the ratio of moment M at any point on body due to hypersonic flow to the product of dynamic pressure, reference area and chord length and is represented as Cm = M_t/(q*A*L_c) or Moment Coefficient = Moment/(Dynamic Pressure*Area for Flow*Chord Length). Moment is an overturning effect (tends to bend or turn the member) created by the force(load) acting on a structural member, Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid, Area for flow decreases velocity increases and vice versa. For subsonic flows, M < 1, the behavior resembles that for incompressible flows & Chord Length is the length of a line segment connecting any two points on the circumference of a circle.

How to calculate Moment Coefficient?

The moment coefficient formula is defined as the ratio of moment M at any point on body due to hypersonic flow to the product of dynamic pressure, reference area and chord length is calculated using Moment Coefficient = Moment/(Dynamic Pressure*Area for Flow*Chord Length). To calculate Moment Coefficient, you need Moment (M_t), Dynamic Pressure (q), Area for Flow (A) & Chord Length (L_c). With our tool, you need to enter the respective value for Moment, Dynamic Pressure, Area for Flow & Chord Length 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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