Yawing moment coefficient Calculator

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✖Yawing moment is the moment acting on the airplane about its yaw axis.ⓘ Yawing Moment [𝑵]			+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%

✖Yawing moment coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis.ⓘ Yawing moment coefficient [C_n]

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Formula

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Yawing moment coefficient

Formula

`"C"_{"n"} = "𝑵"/("q"*"S"*"𝓁")`

Example

`"1.377953"="42N*m"/("10Pa"*"5.08m²"*"0.6m")`

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Yawing moment coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Yawing Moment Coefficient = Yawing Moment/(Dynamic Pressure*Reference Area*Characteristic length)
C_n = 𝑵/(q*S*𝓁)
This formula uses 5 Variables

Variables Used

Yawing Moment Coefficient - Yawing moment coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis.
Yawing Moment - (Measured in Newton Meter) - Yawing moment is the moment acting on the airplane about its yaw 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

Yawing Moment: 42 Newton Meter --> 42 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_n = 𝑵/(q*S*𝓁) --> 42/(10*5.08*0.6)

Evaluating ... ...

C_n = 1.37795275590551

STEP 3: Convert Result to Output's Unit

1.37795275590551 --> No Conversion Required

FINAL ANSWER

1.37795275590551 ≈ 1.377953 <-- Yawing Moment Coefficient

(Calculation completed in 00.004 seconds)

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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

Yawing moment coefficient Formula

Yawing Moment Coefficient = Yawing Moment/(Dynamic Pressure*Reference Area*Characteristic length)
C_n = 𝑵/(q*S*𝓁)

What is yaw axis?

The yaw axis has its origin at the center of gravity and is directed towards the bottom of the aircraft, perpendicular to the wings and the fuselage reference line.

How to Calculate Yawing moment coefficient?

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

How to calculate Yawing moment coefficient using this online calculator? To use this online calculator for Yawing moment coefficient, enter Yawing Moment (𝑵), Dynamic Pressure (q), Reference Area (S) & Characteristic length (𝓁) and hit the calculate button. Here is how the Yawing moment coefficient calculation can be explained with given input values -> 1.377953 = 42/(10*5.08*0.6).

FAQ

What is Yawing moment coefficient?

The Yawing moment coefficient for an aircraft is the function of the yawing moment, dynamic pressure, reference area and characteristic length. and is represented as C_n = 𝑵/(q*S*𝓁) or Yawing Moment Coefficient = Yawing Moment/(Dynamic Pressure*Reference Area*Characteristic length). Yawing moment is the moment acting on the airplane about its yaw 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 Yawing moment coefficient?

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

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