Pitching moment Calculator

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✖Pitching moment coefficient is the coefficient associated with the moment that tends to rotate an airplane pitch axis.ⓘ Pitching moment coefficient [C_m]			+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%
✖The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.ⓘ Reference Area [S]			+10% -10%
✖Characteristic length (used in aerodynamics) is a reference length characteristic of the object under consideration.ⓘ Characteristic length [𝓁]			+10% -10%

✖Pitching moment is the moment acting on the airplane about its pitch axis.ⓘ Pitching moment [𝑴]

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Formula

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Pitching moment

Formula

`"𝑴" = "C"_{"m"}*"q"*"S"*"𝓁"`

Example

`"17.9832N*m"="0.59"*"10Pa"*"5.08m²"*"0.6m"`

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Pitching moment Solution

STEP 0: Pre-Calculation Summary

Formula Used

Pitching moment = Pitching moment coefficient*Dynamic Pressure*Reference Area*Characteristic length
𝑴 = C_m*q*S*𝓁
This formula uses 5 Variables

Variables Used

Pitching moment - (Measured in Newton Meter) - Pitching moment is the moment acting on the airplane about its pitch axis.
Pitching moment coefficient - Pitching moment coefficient is the coefficient associated with the moment that tends to rotate an airplane pitch axis.
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.
Reference Area - (Measured in Square Meter) - The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.
Characteristic length - (Measured in Meter) - Characteristic length (used in aerodynamics) is a reference length characteristic of the object under consideration.

STEP 1: Convert Input(s) to Base Unit

Pitching moment coefficient: 0.59 --> No Conversion Required
Dynamic Pressure: 10 Pascal --> 10 Pascal No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Characteristic length: 0.6 Meter --> 0.6 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

𝑴 = C_m*q*S*𝓁 --> 0.59*10*5.08*0.6

Evaluating ... ...

𝑴 = 17.9832

STEP 3: Convert Result to Output's Unit

17.9832 Newton Meter --> No Conversion Required

FINAL ANSWER

17.9832 Newton Meter <-- Pitching moment

(Calculation completed in 00.004 seconds)

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Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

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< 18 Aircraft Dynamics Nomenclature Calculators

Sideslip angle

Go Sideslip Angle = asin(Velocity along pitch axis/(sqrt((Velocity along Roll Axis^2)+(Velocity along pitch axis^2)+(Velocity along yaw axis^2))))

Mean Aerodynamic Chord for Propeller-Driven Airplane

Go Mean aerodynamic chord = (1/Reference Area)*int(Chord Length^2,x,-Wingspan/2,Wingspan/2)

Pitching moment coefficient

Go Pitching moment coefficient = Pitching moment/(Dynamic Pressure*Reference Area*Characteristic length)

Rolling moment coefficient

Go Rolling moment coefficient = Rolling moment/(Dynamic Pressure*Reference Area*Characteristic length)

Pitching moment

Go Pitching moment = Pitching moment coefficient*Dynamic Pressure*Reference Area*Characteristic length

Yawing moment coefficient

Go Yawing Moment Coefficient = Yawing Moment/(Dynamic Pressure*Reference Area*Characteristic length)

Rolling moment

Go Rolling moment = Rolling moment coefficient*Dynamic Pressure*Reference Area*Characteristic length

Yawing moment

Go Yawing Moment = Yawing Moment Coefficient*Dynamic Pressure*Reference Area*Characteristic length

Normal force coefficient with aerodynamic normal force

Go Normal force coefficient = Aerodynamic Normal Force/(Dynamic Pressure*Reference Area)

Aerodynamic normal force

Go Aerodynamic Normal Force = Normal force coefficient*Dynamic Pressure*Reference Area

Aerodynamic axial force

Go Aerodynamic Axial Force = Axial force coefficient*Dynamic Pressure*Reference Area

Side force coefficient

Go Side force coefficient = Aerodynamic Side Force/(Dynamic Pressure*Reference Area)

Aerodynamic side force

Go Aerodynamic Side Force = Side force coefficient*Dynamic Pressure*Reference Area

Angle of attack

Go Angle of Attack = atan(Velocity along yaw axis/Velocity along Roll Axis)

Velocity along pitch axis for small sideslip angle

Go Velocity along pitch axis = Sideslip Angle*Velocity along Roll Axis

Velocity along roll axis for small sideslip angle

Go Velocity along Roll Axis = Velocity along pitch axis/Sideslip Angle

Velocity along roll axis for small angle of attack

Go Velocity along Roll Axis = Velocity along yaw axis/Angle of Attack

Velocity along yaw axis for small angle of attack

Go Velocity along yaw axis = Velocity along Roll Axis*Angle of Attack

Pitching moment Formula

Pitching moment = Pitching moment coefficient*Dynamic Pressure*Reference Area*Characteristic length
𝑴 = C_m*q*S*𝓁

What is the characteristic length for calculating pitching moment?

Characteristic length is taken as the mean chord length for the pitching moment of an aircraft. In aeronautics, a chord is the imaginary straight line joining the leading edge and trailing edge of an aerofoil. The chord length is the distance between the trailing edge and the point where the chord intersects the leading edge.

How to Calculate Pitching moment?

Pitching moment calculator uses Pitching moment = Pitching moment coefficient*Dynamic Pressure*Reference Area*Characteristic length to calculate the Pitching moment, The Pitching moment for an aircraft is a function of the pitching moment coefficient, dynamic pressure, reference area, and characteristic length. . Pitching moment is denoted by 𝑴 symbol.

How to calculate Pitching moment using this online calculator? To use this online calculator for Pitching moment, enter Pitching moment coefficient (C_m), Dynamic Pressure (q), Reference Area (S) & Characteristic length (𝓁) and hit the calculate button. Here is how the Pitching moment calculation can be explained with given input values -> 17.9832 = 0.59*10*5.08*0.6.

FAQ

What is Pitching moment?

The Pitching moment for an aircraft is a function of the pitching moment coefficient, dynamic pressure, reference area, and characteristic length. and is represented as 𝑴 = C_m*q*S*𝓁 or Pitching moment = Pitching moment coefficient*Dynamic Pressure*Reference Area*Characteristic length. Pitching moment coefficient is the coefficient associated with the moment that tends to rotate an airplane pitch axis, Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid, The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area & Characteristic length (used in aerodynamics) is a reference length characteristic of the object under consideration.

How to calculate Pitching moment?

The Pitching moment for an aircraft is a function of the pitching moment coefficient, dynamic pressure, reference area, and characteristic length. is calculated using Pitching moment = Pitching moment coefficient*Dynamic Pressure*Reference Area*Characteristic length. To calculate Pitching moment, you need Pitching moment coefficient (C_m), Dynamic Pressure (q), Reference Area (S) & Characteristic length (𝓁). With our tool, you need to enter the respective value for Pitching moment coefficient, Dynamic Pressure, Reference Area & Characteristic 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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