Vertical tail area for given moment Calculator

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Static Stability and Control

Aircraft Design

Aircraft Performance

Introduction and Governing Equations

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Directional Stability

Longitudinal Stability

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Vertical Tail Contribution

Aerodynamic Parameters

Wing-Tail Interaction

✖The moment produced by vertical tail is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.ⓘ Moment produced by vertical tail [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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Formula

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Vertical tail area for given moment

Formula

`"S"_{"v"} = "N"_{"v"}/("𝒍"_{"v"}*"C"_{"v"}*("β"+"σ")*"Q"_{"v"})`

Example

`"1.850002m²"="2N*m"/("1.2m"*"0.7rad⁻¹"*("0.05rad"+"0.067rad")*"11Pa")`

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Vertical tail area for given moment Solution

STEP 0: Pre-Calculation Summary

Formula Used

Vertical tail area = Moment produced by vertical tail/(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.
Moment produced by vertical tail - (Measured in Newton Meter) - The moment produced by vertical tail 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

Moment produced by vertical tail: 2 Newton Meter --> 2 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) --> 2/(1.2*0.7*(0.05+0.067)*11)

Evaluating ... ...

S_v = 1.85000185000185

STEP 3: Convert Result to Output's Unit

1.85000185000185 Square Meter --> No Conversion Required

FINAL ANSWER

1.85000185000185 ≈ 1.850002 Square Meter <-- Vertical tail area

(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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National Institute Of Technology (NIT), Hamirpur

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< 24 Vertical Tail Contribution Calculators

Vertical tail moment arm for given yawing moment coefficient

Go Vertical tail moment arm = Yawing moment coefficient/(Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)/(Reference Area*Wingspan*Wing dynamic pressure))

Vertical tail area for given yawing moment coefficient

Go 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))

Vertical tail lift curve slope for given yawing moment coefficient

Go Vertical tail Lift curve slope = Yawing moment coefficient*Reference Area*Wingspan*Wing dynamic pressure/(Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*(Sideslip angle+Sidewash angle))

Vertical tail moment arm for given lift curve slope

Go Vertical tail moment arm = Moment produced by vertical tail/(Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)*Vertical tail dynamic pressure*Vertical tail area)

Vertical tail lift curve slope for given moment

Go Vertical tail Lift curve slope = Moment produced by vertical tail/(Vertical tail moment arm*(Sideslip angle+Sidewash angle)*Vertical tail dynamic pressure*Vertical tail area)

Vertical tail area for given moment

Go Vertical tail area = Moment produced by vertical tail/(Vertical tail moment arm*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)*Vertical tail dynamic pressure)

Moment produced by vertical tail for given lift curve slope

Go Moment produced by vertical tail = Vertical tail moment arm*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)*Vertical tail dynamic pressure*Vertical tail area

Vertical tail lift curve slope for given yawing moment coefficient and Vertical Tail Efficiency

Go Vertical tail Lift curve slope = Yawing moment coefficient/(Vertical Tail Volume Ratio*Vertical tail efficiency*(Sideslip angle+Sidewash angle))

Vertical tail volume ratio for given yawing moment coefficient

Go Vertical Tail Volume Ratio = Yawing moment coefficient/(Vertical tail efficiency*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle))

Vertical tail efficiency for given yawing moment coefficient

Go Vertical tail efficiency = Yawing moment coefficient/(Vertical Tail Volume Ratio*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle))

Vertical tail area for given vertical tail side force

Go Vertical tail area = -(Vertical Tail Side Force)/(Vertical tail Lift curve slope*Vertical tail angle of attack*Vertical tail dynamic pressure)

Vertical tail dynamic pressure for given vertical tail side force

Go Vertical tail dynamic pressure = -Vertical Tail Side Force/(Vertical tail Lift curve slope*Vertical tail angle of attack*Vertical tail area)

Vertical tail angle of attack for given vertical tail side force

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

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

Go Vertical Tail Side Force = -Vertical tail Lift curve slope*Vertical tail angle of attack*Vertical tail area*Vertical tail dynamic pressure

Moment produced by vertical tail for given moment coefficient

Go Moment produced by vertical tail = Yawing moment coefficient*Wing dynamic pressure*Wingspan*Reference Area

Vertical tail volume ratio

Go Vertical Tail Volume Ratio = Vertical tail moment arm*Vertical tail area/(Reference Area*Wingspan)

Vertical tail moment arm for given vertical tail volume ratio

Go Vertical tail moment arm = Vertical Tail Volume Ratio*Reference Area*Wingspan/Vertical tail area

Vertical tail area for given vertical tail volume ratio

Go Vertical tail area = Vertical Tail Volume Ratio*Reference Area*Wingspan/Vertical tail moment arm

Vertical tail moment arm for given side force

Go Vertical tail moment arm = -Moment produced by vertical tail/Vertical Tail Side Force

Moment produced by vertical tail for given side force

Go Moment produced by vertical tail = Vertical tail moment arm*Vertical Tail Side Force

Vertical tail side force for given moment

Go Vertical Tail Side Force = Moment produced by vertical tail/Vertical tail moment arm

Vertical tail efficiency

Go Vertical tail efficiency = Vertical tail dynamic pressure/Wing dynamic pressure

Vertical tail angle of attack

Go Vertical tail angle of attack = Sidewash angle+Sideslip angle

Vertical tail area for given moment Formula

Which control surface is primarily used for spin recovery?

Studies have indicated that deflections of the rudder and elevator are the predominant control-surface movements required for spin recovery, the use of either or both depending on the weight distribution within the airplane.

How to Calculate Vertical tail area for given moment?

Vertical tail area for given moment calculator uses Vertical tail area = Moment produced by vertical tail/(Vertical tail moment arm*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)*Vertical tail dynamic pressure) to calculate the Vertical tail area, The Vertical tail area for given moment produced by the vertical tail is a function of the vertical tail's moment arm, lift curve slope, dynamic pressure, sideslip angle, and sidewash angle. 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 Moment produced by vertical tail (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 -> 1.850002 = 2/(1.2*0.7*(0.05+0.067)*11).

FAQ

What is Vertical tail area for given moment?

The Vertical tail area for given moment produced by the vertical tail is a function of the vertical tail's moment arm, lift curve slope, dynamic pressure, sideslip angle, and sidewash angle and is represented as S_v = N_v/(𝒍_v*C_v*(β+σ)*Q_v) or Vertical tail area = Moment produced by vertical tail/(Vertical tail moment arm*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)*Vertical tail dynamic pressure). The moment produced by vertical tail 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?

The Vertical tail area for given moment produced by the vertical tail is a function of the vertical tail's moment arm, lift curve slope, dynamic pressure, sideslip angle, and sidewash angle is calculated using Vertical tail area = Moment produced by vertical tail/(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 Moment produced by vertical tail (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 Moment produced by vertical tail, 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 Moment produced by vertical tail, 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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