Vertical Tail Area for given Vertical Tail Side Force Calculator

✖Vertical Tail Side Force is the side force acting on the vertical tail of an aircraft.ⓘ Vertical Tail Side Force [Y_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%
✖Vertical Tail Angle of Attack is the angle of attack experienced by the vertical tailplane of an aircraft.ⓘ Vertical Tail Angle of Attack [α_v]			+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 Vertical Tail Side Force [S_v]

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Vertical Tail Area for given Vertical Tail Side Force Solution

STEP 0: Pre-Calculation Summary

Formula Used

Vertical Tail Area = -(Vertical Tail Side Force)/(Vertical Tail Lift Curve Slope*Vertical Tail Angle of Attack*Vertical Tail Dynamic Pressure)
S_v = -(Y_v)/(C_v*α_v*Q_v)
This formula uses 5 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 Side Force - (Measured in Newton) - Vertical Tail Side Force is the side force acting on the vertical tail of an 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.
Vertical Tail Angle of Attack - (Measured in Radian) - Vertical Tail Angle of Attack is the angle of attack experienced by the vertical tailplane of an aircraft.
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 Side Force: -4.235 Newton --> -4.235 Newton No Conversion Required
Vertical Tail Lift Curve Slope: 0.7 1 per Radian --> 0.7 1 per Radian No Conversion Required
Vertical Tail Angle of Attack: 0.117 Radian --> 0.117 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 = -(Y_v)/(C_v*α_v*Q_v) --> -((-4.235))/(0.7*0.117*11)

Evaluating ... ...

S_v = 4.7008547008547

STEP 3: Convert Result to Output's Unit

4.7008547008547 Square Meter --> No Conversion Required

FINAL ANSWER

4.7008547008547 ≈ 4.700855 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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< 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 Vertical Tail Side Force Formula

LaTeX Go

Vertical Tail Area = -(Vertical Tail Side Force)/(Vertical Tail Lift Curve Slope*Vertical Tail Angle of Attack*Vertical Tail Dynamic Pressure)
S_v = -(Y_v)/(C_v*α_v*Q_v)

What is P factor in aviation?

P-factor, also known as asymmetric blade effect and asymmetric disc effect, is an aerodynamic phenomenon experienced by a moving propeller, where the propeller's center of thrust moves off-center when the aircraft is at a high angle of attack.

How to Calculate Vertical Tail Area for given Vertical Tail Side Force?

Vertical Tail Area for given Vertical Tail Side Force calculator uses Vertical Tail Area = -(Vertical Tail Side Force)/(Vertical Tail Lift Curve Slope*Vertical Tail Angle of Attack*Vertical Tail Dynamic Pressure) to calculate the Vertical Tail Area, Vertical Tail Area for given Vertical Tail Side Force is a measure of the surface area of the vertical tail required to produce a given side force, taking into account the lift curve slope, angle of attack, and dynamic pressure. Vertical Tail Area is denoted by S_v symbol.

How to calculate Vertical Tail Area for given Vertical Tail Side Force using this online calculator? To use this online calculator for Vertical Tail Area for given Vertical Tail Side Force, enter Vertical Tail Side Force (Y_v), Vertical Tail Lift Curve Slope (C_v), Vertical Tail Angle of Attack (α_v) & Vertical Tail Dynamic Pressure (Q_v) and hit the calculate button. Here is how the Vertical Tail Area for given Vertical Tail Side Force calculation can be explained with given input values -> 4.700855 = -((-4.235))/(0.7*0.117*11).

FAQ

What is Vertical Tail Area for given Vertical Tail Side Force?

Vertical Tail Area for given Vertical Tail Side Force is a measure of the surface area of the vertical tail required to produce a given side force, taking into account the lift curve slope, angle of attack, and dynamic pressure and is represented as S_v = -(Y_v)/(C_v*α_v*Q_v) or Vertical Tail Area = -(Vertical Tail Side Force)/(Vertical Tail Lift Curve Slope*Vertical Tail Angle of Attack*Vertical Tail Dynamic Pressure). Vertical Tail Side Force is the side force acting on the vertical tail of an aircraft, The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft, Vertical Tail Angle of Attack is the angle of attack experienced by the vertical tailplane of an aircraft & Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft.

How to calculate Vertical Tail Area for given Vertical Tail Side Force?

Vertical Tail Area for given Vertical Tail Side Force is a measure of the surface area of the vertical tail required to produce a given side force, taking into account the lift curve slope, angle of attack, and dynamic pressure is calculated using Vertical Tail Area = -(Vertical Tail Side Force)/(Vertical Tail Lift Curve Slope*Vertical Tail Angle of Attack*Vertical Tail Dynamic Pressure). To calculate Vertical Tail Area for given Vertical Tail Side Force, you need Vertical Tail Side Force (Y_v), Vertical Tail Lift Curve Slope (C_v), Vertical Tail Angle of Attack (α_v) & Vertical Tail Dynamic Pressure (Q_v). With our tool, you need to enter the respective value for Vertical Tail Side Force, Vertical Tail Lift Curve Slope, Vertical Tail Angle of Attack & 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 Side Force, Vertical Tail Lift Curve Slope, Vertical Tail Angle of Attack & 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 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))
Vertical Tail Area = Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure)

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