Pitching moment coefficient Calculator

↳

⤿

Introduction and Governing Equations

Aircraft Design

Aircraft Performance

Static Stability and Control

⤿

Aircraft Dynamics Nomenclature

Atmosphere and Gas Properties

Lift and Drag Polar

Preliminary Aerodynamics

✖Pitching moment is the moment acting on the airplane about its pitch axis.ⓘ Pitching moment [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 coefficient is the coefficient associated with the moment that tends to rotate an airplane pitch axis.ⓘ Pitching moment coefficient [C_m]

⎘ Copy

👎

Formula

✖

Pitching moment coefficient

Formula

`"C"_{"m"} = "𝑴"/("q"*"S"*"𝓁")`

Example

`"0.018045"="0.55N*m"/("10Pa"*"5.08m²"*"0.6m")`

Calculator

LaTeX

Reset

👍

Download Physics Formula PDF

Pitching moment coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

Pitching moment coefficient - Pitching moment coefficient is the coefficient associated with the moment that tends to rotate an airplane pitch axis.
Pitching moment - (Measured in Newton Meter) - Pitching moment is the moment acting on the airplane about its 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: 0.55 Newton Meter --> 0.55 Newton Meter 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

C_m = 𝑴/(q*S*𝓁) --> 0.55/(10*5.08*0.6)

Evaluating ... ...

C_m = 0.0180446194225722

STEP 3: Convert Result to Output's Unit

0.0180446194225722 --> No Conversion Required

FINAL ANSWER

0.0180446194225722 ≈ 0.018045 <-- Pitching moment coefficient

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Introduction and Governing Equations » Aircraft Dynamics Nomenclature » Pitching moment coefficient

Credits

Created by Vinay Mishra

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

Vinay Mishra has created this Calculator and 300+ more calculators!

Verified by Shikha Maurya

Indian Institute of Technology (IIT), Bombay

Shikha Maurya has verified this Calculator and 200+ more calculators!

< 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 coefficient Formula

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

What is pitch axis?

The pitch axis (also called transverse or lateral axis) has its origin at the center of gravity and is directed to the right, parallel to a line drawn from wingtip to wingtip.

How to Calculate Pitching moment coefficient?

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

How to calculate Pitching moment coefficient using this online calculator? To use this online calculator for Pitching moment coefficient, enter Pitching moment (𝑴), Dynamic Pressure (q), Reference Area (S) & Characteristic length (𝓁) and hit the calculate button. Here is how the Pitching moment coefficient calculation can be explained with given input values -> 0.018045 = 0.55/(10*5.08*0.6).

FAQ

What is Pitching moment coefficient?

The Pitching moment coefficient for an aircraft is the function of the pitching moment, dynamic pressure, reference area and characteristic length. and is represented as C_m = 𝑴/(q*S*𝓁) or Pitching moment coefficient = Pitching moment/(Dynamic Pressure*Reference Area*Characteristic length). Pitching moment is the moment acting on the airplane about its 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 coefficient?

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

Home

FREE PDFs

🔍 Search