Moment Produced by Vertical Tail for given Moment Coefficient Calculator

✖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]			+10% -10%
✖Wing Dynamic Pressure is the dynamic pressure associated with the wing of an aircraft.ⓘ Wing Dynamic Pressure [Q_w]			+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%
✖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%

✖Vertical Tail Moment is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.ⓘ Moment Produced by Vertical Tail for given Moment Coefficient [N_v]

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Moment Produced by Vertical Tail for given Moment Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Vertical Tail Moment = Yawing Moment Coefficient*Wing Dynamic Pressure*Wingspan*Reference Area
N_v = C_n*Q_w*b*S
This formula uses 5 Variables

Variables Used

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.
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.
Wing Dynamic Pressure - (Measured in Pascal) - Wing Dynamic Pressure is the dynamic pressure associated with the wing of an aircraft.
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.
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.

STEP 1: Convert Input(s) to Base Unit

Yawing Moment Coefficient: 1.4 --> No Conversion Required
Wing Dynamic Pressure: 0.66 Pascal --> 0.66 Pascal No Conversion Required
Wingspan: 1.15 Meter --> 1.15 Meter No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

N_v = C_n*Q_w*b*S --> 1.4*0.66*1.15*5.08

Evaluating ... ...

N_v = 5.398008

STEP 3: Convert Result to Output's Unit

5.398008 Newton Meter --> No Conversion Required

FINAL ANSWER

5.398008 Newton Meter <-- Vertical Tail 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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< Vertical Tail Contribution Calculators

Vertical Tail Angle of Attack for given Vertical Tail Side Force

LaTeX Go Vertical Tail Angle of Attack = -(Vertical Tail Side Force/(Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area))

Vertical Tail Lift Curve Slope

LaTeX Go Vertical Tail Lift Curve Slope = -(Vertical Tail Side Force/(Vertical Tail Angle of Attack*Vertical Tail Dynamic Pressure*Vertical Tail Area))

Vertical Tail Side Force

LaTeX Go Vertical Tail Side Force = -Vertical Tail Lift Curve Slope*Vertical Tail Angle of Attack*Vertical Tail Area*Vertical Tail Dynamic Pressure

Vertical Tail Angle of Attack

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

Moment Produced by Vertical Tail for given Moment Coefficient Formula

LaTeX Go

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

What is tail down force?

The elevator (or stabilator) of an aircraft balances out the torque by creating another downward force, called tail-down force, by generating torque in the opposite direction. Essentially, the tail is an 'upside down' wing that generates lift downward.

How to Calculate Moment Produced by Vertical Tail for given Moment Coefficient?

Moment Produced by Vertical Tail for given Moment Coefficient calculator uses Vertical Tail Moment = Yawing Moment Coefficient*Wing Dynamic Pressure*Wingspan*Reference Area to calculate the Vertical Tail Moment, Moment Produced by Vertical Tail for given Moment Coefficient is a measure of the rotational force generated by the vertical tail of an aircraft, calculated by multiplying the yawing moment coefficient, wing dynamic pressure, wingspan, and reference area. Vertical Tail Moment is denoted by N_v symbol.

How to calculate Moment Produced by Vertical Tail for given Moment Coefficient using this online calculator? To use this online calculator for Moment Produced by Vertical Tail for given Moment Coefficient, enter Yawing Moment Coefficient (C_n), Wing Dynamic Pressure (Q_w), Wingspan (b) & Reference Area (S) and hit the calculate button. Here is how the Moment Produced by Vertical Tail for given Moment Coefficient calculation can be explained with given input values -> 5.398008 = 1.4*0.66*1.15*5.08.

FAQ

What is Moment Produced by Vertical Tail for given Moment Coefficient?

Moment Produced by Vertical Tail for given Moment Coefficient is a measure of the rotational force generated by the vertical tail of an aircraft, calculated by multiplying the yawing moment coefficient, wing dynamic pressure, wingspan, and reference area and is represented as N_v = C_n*Q_w*b*S or Vertical Tail Moment = Yawing Moment Coefficient*Wing Dynamic Pressure*Wingspan*Reference Area. Yawing Moment Coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis, Wing Dynamic Pressure is the dynamic pressure associated with the wing of an aircraft, The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip & 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.

How to calculate Moment Produced by Vertical Tail for given Moment Coefficient?

Moment Produced by Vertical Tail for given Moment Coefficient is a measure of the rotational force generated by the vertical tail of an aircraft, calculated by multiplying the yawing moment coefficient, wing dynamic pressure, wingspan, and reference area is calculated using Vertical Tail Moment = Yawing Moment Coefficient*Wing Dynamic Pressure*Wingspan*Reference Area. To calculate Moment Produced by Vertical Tail for given Moment Coefficient, you need Yawing Moment Coefficient (C_n), Wing Dynamic Pressure (Q_w), Wingspan (b) & Reference Area (S). With our tool, you need to enter the respective value for Yawing Moment Coefficient, Wing Dynamic Pressure, Wingspan & Reference Area 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 Vertical Tail Moment?

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

Vertical Tail Moment = -(Vertical Tail Moment Arm*Vertical Tail Side Force)
Vertical Tail Moment = Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area

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