Vertical Tail Area for given Moment 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%
✖The Vertical Tail Moment Arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft.ⓘ Vertical Tail Moment Arm [𝒍_v]			+10% -10%
✖The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft.ⓘ Vertical Tail Lift Curve Slope [C_v]			+10% -10%
✖The Sideslip Angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind.ⓘ Sideslip Angle [β]			+10% -10%
✖Sidewash Angle is caused by the flow field distortion due to the wings and fuselage. It is analogous to the downwash angle for the horizontal tailplane.ⓘ Sidewash Angle [σ]			+10% -10%
✖Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft.ⓘ Vertical Tail Dynamic Pressure [Q_v]			+10% -10%

✖The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline.ⓘ Vertical Tail Area for given Moment [S_v]

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Vertical Tail Area for given Moment Solution

STEP 0: Pre-Calculation Summary

Formula Used

Vertical Tail Area = Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure)
S_v = N_v/(𝒍_v*C_v*(β+σ)*Q_v)
This formula uses 7 Variables

Variables Used

Vertical Tail Area - (Measured in Square Meter) - The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline.
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.
Vertical Tail Moment Arm - (Measured in Meter) - The Vertical Tail Moment Arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft.
Vertical Tail Lift Curve Slope - (Measured in 1 per Radian) - The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft.
Sideslip Angle - (Measured in Radian) - The Sideslip Angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind.
Sidewash Angle - (Measured in Radian) - Sidewash Angle is caused by the flow field distortion due to the wings and fuselage. It is analogous to the downwash angle for the horizontal tailplane.
Vertical Tail Dynamic Pressure - (Measured in Pascal) - Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft.

STEP 1: Convert Input(s) to Base Unit

Vertical Tail Moment: 5.4 Newton Meter --> 5.4 Newton Meter No Conversion Required
Vertical Tail Moment Arm: 1.2 Meter --> 1.2 Meter No Conversion Required
Vertical Tail Lift Curve Slope: 0.7 1 per Radian --> 0.7 1 per Radian No Conversion Required
Sideslip Angle: 0.05 Radian --> 0.05 Radian No Conversion Required
Sidewash Angle: 0.067 Radian --> 0.067 Radian No Conversion Required
Vertical Tail Dynamic Pressure: 11 Pascal --> 11 Pascal No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

S_v = N_v/(𝒍_v*C_v*(β+σ)*Q_v) --> 5.4/(1.2*0.7*(0.05+0.067)*11)

Evaluating ... ...

S_v = 4.995004995005

STEP 3: Convert Result to Output's Unit

4.995004995005 Square Meter --> No Conversion Required

FINAL ANSWER

4.995004995005 ≈ 4.995005 Square Meter <-- Vertical Tail Area

(Calculation completed in 00.007 seconds)

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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 Anshika Arya

National Institute Of Technology (NIT), Hamirpur

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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

Vertical Tail Area for given Moment Formula

LaTeX Go

Vertical Tail Area = Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure)
S_v = N_v/(𝒍_v*C_v*(β+σ)*Q_v)

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How to Calculate Vertical Tail Area for given Moment?

Vertical Tail Area for given Moment calculator uses Vertical Tail Area = Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure) to calculate the Vertical Tail Area, Vertical Tail Area for Given Moment is a measure of the surface area of the vertical tail required to produce a specific moment, taking into account the moment arm, lift curve slope, sideslip angle, sidewash angle, and dynamic pressure, ensuring stability and control of an aircraft in flight. Vertical Tail Area is denoted by S_v symbol.

How to calculate Vertical Tail Area for given Moment using this online calculator? To use this online calculator for Vertical Tail Area for given Moment, enter Vertical Tail Moment (N_v), Vertical Tail Moment Arm (𝒍_v), Vertical Tail Lift Curve Slope (C_v), Sideslip Angle (β), Sidewash Angle (σ) & Vertical Tail Dynamic Pressure (Q_v) and hit the calculate button. Here is how the Vertical Tail Area for given Moment calculation can be explained with given input values -> 4.995005 = 5.4/(1.2*0.7*(0.05+0.067)*11).

FAQ

What is Vertical Tail Area for given Moment?

Vertical Tail Area for Given Moment is a measure of the surface area of the vertical tail required to produce a specific moment, taking into account the moment arm, lift curve slope, sideslip angle, sidewash angle, and dynamic pressure, ensuring stability and control of an aircraft in flight and is represented as S_v = N_v/(𝒍_v*C_v*(β+σ)*Q_v) or Vertical Tail Area = Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure). Vertical Tail Moment is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it, The Vertical Tail Moment Arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft, The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft, The Sideslip Angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind, Sidewash Angle is caused by the flow field distortion due to the wings and fuselage. It is analogous to the downwash angle for the horizontal tailplane & Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft.

How to calculate Vertical Tail Area for given Moment?

Vertical Tail Area for Given Moment is a measure of the surface area of the vertical tail required to produce a specific moment, taking into account the moment arm, lift curve slope, sideslip angle, sidewash angle, and dynamic pressure, ensuring stability and control of an aircraft in flight is calculated using Vertical Tail Area = Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure). To calculate Vertical Tail Area for given Moment, you need Vertical Tail Moment (N_v), Vertical Tail Moment Arm (𝒍_v), Vertical Tail Lift Curve Slope (C_v), Sideslip Angle (β), Sidewash Angle (σ) & Vertical Tail Dynamic Pressure (Q_v). With our tool, you need to enter the respective value for Vertical Tail Moment, Vertical Tail Moment Arm, Vertical Tail Lift Curve Slope, Sideslip Angle, Sidewash Angle & Vertical Tail Dynamic Pressure 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 Area?

In this formula, Vertical Tail Area uses Vertical Tail Moment, Vertical Tail Moment Arm, Vertical Tail Lift Curve Slope, Sideslip Angle, Sidewash Angle & Vertical Tail Dynamic Pressure. We can use 3 other way(s) to calculate the same, which is/are as follows -

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

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