Yawing Moment Coefficient using Wingspan Calculator

✖Vertical Tail Moment is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.ⓘ Vertical Tail Moment [N_v]			+10% -10%
✖Wing Dynamic Pressure is the dynamic pressure associated with the wing of an aircraft.ⓘ Wing Dynamic Pressure [Q_w]			+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%
✖The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.ⓘ Wingspan [b]			+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 using Wingspan [C_n]

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Yawing Moment Coefficient using Wingspan Solution

STEP 0: Pre-Calculation Summary

Formula Used

Yawing Moment Coefficient = Vertical Tail Moment/(Wing Dynamic Pressure*Reference Area*Wingspan)
C_n = N_v/(Q_w*S*b)
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.
Vertical Tail Moment - (Measured in Newton Meter) - Vertical Tail Moment is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.
Wing Dynamic Pressure - (Measured in Pascal) - Wing Dynamic Pressure is the dynamic pressure associated with the wing of an aircraft.
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.
Wingspan - (Measured in Meter) - The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.

STEP 1: Convert Input(s) to Base Unit

Vertical Tail Moment: 5.4 Newton Meter --> 5.4 Newton Meter No Conversion Required
Wing Dynamic Pressure: 0.66 Pascal --> 0.66 Pascal No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Wingspan: 1.15 Meter --> 1.15 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_n = N_v/(Q_w*S*b) --> 5.4/(0.66*5.08*1.15)

Evaluating ... ...

C_n = 1.40051663502537

STEP 3: Convert Result to Output's Unit

1.40051663502537 --> No Conversion Required

FINAL ANSWER

1.40051663502537 ≈ 1.400517 <-- Yawing Moment Coefficient

(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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< Aerodynamic Parameters Calculators

Sidewash Angle for given Moment Produced by Vertical Tail

LaTeX Go Sidewash Angle = (Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area))-Sideslip Angle

Yawing Moment Coefficient using Wingspan

LaTeX Go Yawing Moment Coefficient = Vertical Tail Moment/(Wing Dynamic Pressure*Reference Area*Wingspan)

Sideslip Angle for Aircraft

LaTeX Go Sideslip Angle = Vertical Tail Angle of Attack-Sidewash Angle

Sidewash angle

LaTeX Go Sidewash Angle = Vertical Tail Angle of Attack-Sideslip Angle

Yawing Moment Coefficient using Wingspan Formula

LaTeX Go

Yawing Moment Coefficient = Vertical Tail Moment/(Wing Dynamic Pressure*Reference Area*Wingspan)
C_n = N_v/(Q_w*S*b)

Why is yaw important?

Rudder turns or yawing at low speed can result in one wing stalling before the other one, causing the potential of a spin. Additionally, yawing causes one wing to produce more lift than the opposite wing, causing a roll. Controlling the roll without the yaw is a better way to turn the airplane.

How to Calculate Yawing Moment Coefficient using Wingspan?

Yawing Moment Coefficient using Wingspan calculator uses Yawing Moment Coefficient = Vertical Tail Moment/(Wing Dynamic Pressure*Reference Area*Wingspan) to calculate the Yawing Moment Coefficient, Yawing Moment Coefficient using Wingspan formula is a measure of the rotational force that causes an aircraft to rotate around its vertical axis, calculated by dividing the moment produced by the vertical tail by the product of wing dynamic pressure, reference area, and wingspan, this coefficient is a crucial factor in evaluating an aircraft's directional stability and control characteristics. Yawing Moment Coefficient is denoted by C_n symbol.

How to calculate Yawing Moment Coefficient using Wingspan using this online calculator? To use this online calculator for Yawing Moment Coefficient using Wingspan, enter Vertical Tail Moment (N_v), Wing Dynamic Pressure (Q_w), Reference Area (S) & Wingspan (b) and hit the calculate button. Here is how the Yawing Moment Coefficient using Wingspan calculation can be explained with given input values -> 1.400517 = 5.4/(0.66*5.08*1.15).

FAQ

What is Yawing Moment Coefficient using Wingspan?

Yawing Moment Coefficient using Wingspan formula is a measure of the rotational force that causes an aircraft to rotate around its vertical axis, calculated by dividing the moment produced by the vertical tail by the product of wing dynamic pressure, reference area, and wingspan, this coefficient is a crucial factor in evaluating an aircraft's directional stability and control characteristics and is represented as C_n = N_v/(Q_w*S*b) or Yawing Moment Coefficient = Vertical Tail Moment/(Wing Dynamic Pressure*Reference Area*Wingspan). Vertical Tail Moment is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it, Wing Dynamic Pressure is the dynamic pressure associated with the wing of an aircraft, 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 & The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.

How to calculate Yawing Moment Coefficient using Wingspan?

Yawing Moment Coefficient using Wingspan formula is a measure of the rotational force that causes an aircraft to rotate around its vertical axis, calculated by dividing the moment produced by the vertical tail by the product of wing dynamic pressure, reference area, and wingspan, this coefficient is a crucial factor in evaluating an aircraft's directional stability and control characteristics is calculated using Yawing Moment Coefficient = Vertical Tail Moment/(Wing Dynamic Pressure*Reference Area*Wingspan). To calculate Yawing Moment Coefficient using Wingspan, you need Vertical Tail Moment (N_v), Wing Dynamic Pressure (Q_w), Reference Area (S) & Wingspan (b). With our tool, you need to enter the respective value for Vertical Tail Moment, Wing Dynamic Pressure, Reference Area & Wingspan and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Yawing Moment Coefficient?

In this formula, Yawing Moment Coefficient uses Vertical Tail Moment, Wing Dynamic Pressure, Reference Area & Wingspan. We can use 2 other way(s) to calculate the same, which is/are as follows -

Yawing Moment Coefficient = Vertical Tail Moment Arm*Vertical Tail Area*Vertical Tail Dynamic Pressure*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)/(Reference Area*Wingspan*Wing Dynamic Pressure)
Yawing Moment Coefficient = Vertical Tail Volume Ratio*Vertical Tail Efficiency*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)

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