Vertical Tail Side Force Calculator

✖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%
✖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 [S_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%

✖Vertical Tail Side Force is the side force acting on the vertical tail of an aircraft.ⓘ Vertical Tail Side Force [Y_v]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Vertical Tail Contribution Formulas PDF PDF Image

Vertical Tail Side Force Solution

STEP 0: Pre-Calculation Summary

Formula Used

Vertical Tail Side Force = -Vertical Tail Lift Curve Slope*Vertical Tail Angle of Attack*Vertical Tail Area*Vertical Tail Dynamic Pressure
Y_v = -C_v*α_v*S_v*Q_v
This formula uses 5 Variables

Variables Used

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 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 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 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 Area: 5 Square Meter --> 5 Square Meter No Conversion Required
Vertical Tail Dynamic Pressure: 11 Pascal --> 11 Pascal No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Y_v = -C_v*α_v*S_v*Q_v --> -0.7*0.117*5*11

Evaluating ... ...

Y_v = -4.5045

STEP 3: Convert Result to Output's Unit

-4.5045 Newton --> No Conversion Required

FINAL ANSWER

-4.5045 Newton <-- Vertical Tail Side Force

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Static Stability and Control » Directional Stability » Aerospace » Vertical Tail Contribution » Vertical Tail Side Force

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

Anshika Arya has verified this Calculator and 2500+ more calculators!

< 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 Side Force Formula

LaTeX Go

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

How can Planes improve directional stability?

The larger the tail surface area, the larger the moment that is generated, and the greater the directional stability.

How to Calculate Vertical Tail Side Force?

Vertical Tail Side Force calculator uses Vertical Tail Side Force = -Vertical Tail Lift Curve Slope*Vertical Tail Angle of Attack*Vertical Tail Area*Vertical Tail Dynamic Pressure to calculate the Vertical Tail Side Force, Vertical Tail Side Force is a measure of the sideways force exerted on an aircraft's vertical tail, indicating its ability to resist yaw and maintain directional stability during flight, it is dependent on the vertical tail's lift curve slope, angle of attack, area, and dynamic pressure, and is crucial in ensuring the aircraft's overall stability and control during various flight regimes. Vertical Tail Side Force is denoted by Y_v symbol.

How to calculate Vertical Tail Side Force using this online calculator? To use this online calculator for Vertical Tail Side Force, enter Vertical Tail Lift Curve Slope (C_v), Vertical Tail Angle of Attack (α_v), Vertical Tail Area (S_v) & Vertical Tail Dynamic Pressure (Q_v) and hit the calculate button. Here is how the Vertical Tail Side Force calculation can be explained with given input values -> -4.5045 = -0.7*0.117*5*11.

FAQ

What is Vertical Tail Side Force?

Vertical Tail Side Force is a measure of the sideways force exerted on an aircraft's vertical tail, indicating its ability to resist yaw and maintain directional stability during flight, it is dependent on the vertical tail's lift curve slope, angle of attack, area, and dynamic pressure, and is crucial in ensuring the aircraft's overall stability and control during various flight regimes and is represented as Y_v = -C_v*α_v*S_v*Q_v or Vertical Tail Side Force = -Vertical Tail Lift Curve Slope*Vertical Tail Angle of Attack*Vertical Tail Area*Vertical Tail Dynamic Pressure. 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, The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline & Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft.

How to calculate Vertical Tail Side Force?

Vertical Tail Side Force is a measure of the sideways force exerted on an aircraft's vertical tail, indicating its ability to resist yaw and maintain directional stability during flight, it is dependent on the vertical tail's lift curve slope, angle of attack, area, and dynamic pressure, and is crucial in ensuring the aircraft's overall stability and control during various flight regimes is calculated using Vertical Tail Side Force = -Vertical Tail Lift Curve Slope*Vertical Tail Angle of Attack*Vertical Tail Area*Vertical Tail Dynamic Pressure. To calculate Vertical Tail Side Force, you need Vertical Tail Lift Curve Slope (C_v), Vertical Tail Angle of Attack (α_v), Vertical Tail Area (S_v) & Vertical Tail Dynamic Pressure (Q_v). With our tool, you need to enter the respective value for Vertical Tail Lift Curve Slope, Vertical Tail Angle of Attack, Vertical Tail Area & 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 Side Force?

In this formula, Vertical Tail Side Force uses Vertical Tail Lift Curve Slope, Vertical Tail Angle of Attack, Vertical Tail Area & Vertical Tail Dynamic Pressure. We can use 1 other way(s) to calculate the same, which is/are as follows -

Vertical Tail Side Force = -(Vertical Tail Moment/Vertical Tail Moment Arm)

Home

FREE PDFs

🔍 Search