Vertical Tail Angle of Attack Calculator

✖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%
✖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%

✖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]

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Formula

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Vertical Tail Angle of Attack

Formula

`"α"_{"v"} = "σ"+"β"`

Example

`"0.117rad"="0.067rad"+"0.05rad"`

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Vertical Tail Angle of Attack Solution

STEP 0: Pre-Calculation Summary

Formula Used

Vertical Tail Angle of Attack = Sidewash Angle+Sideslip Angle
α_v = σ+β
This formula uses 3 Variables

Variables Used

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.
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.
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.

STEP 1: Convert Input(s) to Base Unit

Sidewash Angle: 0.067 Radian --> 0.067 Radian No Conversion Required
Sideslip Angle: 0.05 Radian --> 0.05 Radian No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

α_v = σ+β --> 0.067+0.05

Evaluating ... ...

α_v = 0.117

STEP 3: Convert Result to Output's Unit

0.117 Radian --> No Conversion Required

FINAL ANSWER

0.117 Radian <-- Vertical Tail Angle of Attack

(Calculation completed in 00.020 seconds)

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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 Shikha Maurya

Indian Institute of Technology (IIT), Bombay

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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 = Vertical Tail Moment/(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 = Vertical Tail Moment/(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 = Vertical Tail Moment/(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 Vertical Tail Moment = 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 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 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 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 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

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

Moment Produced by Vertical Tail for given Moment Coefficient

Go Vertical Tail Moment = Yawing Moment Coefficient*Wing Dynamic Pressure*Wingspan*Reference Area

Vertical Tail Efficiency

Go Vertical Tail Efficiency = Vertical Tail Dynamic Pressure/Wing Dynamic Pressure

Moment Produced by Vertical Tail for given Side Force

Go Vertical Tail Moment = -(Vertical Tail Moment Arm*Vertical Tail Side Force)

Vertical Tail Side Force for Given Moment

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

Vertical Tail Moment Arm for given Side Force

Go Vertical Tail Moment Arm = -Vertical Tail Moment/Vertical Tail Side Force

Vertical Tail Angle of Attack

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

Vertical Tail Angle of Attack Formula

Vertical Tail Angle of Attack = Sidewash Angle+Sideslip Angle
α_v = σ+β

Why do planes land at an angle?

Crab angle is removed before the touchdown to reduce the side loads on the airplane's landing gear. The aircraft approaches the runway on a steady sideslip, maintains the sideslip during the flare, and touch down.

How to Calculate Vertical Tail Angle of Attack?

Vertical Tail Angle of Attack calculator uses Vertical Tail Angle of Attack = Sidewash Angle+Sideslip Angle to calculate the Vertical Tail Angle of Attack, Vertical Tail Angle of Attack is a measure of the angle between the vertical tail's aerodynamic force and the aircraft's flight path, calculated by adding the sidewash angle and sideslip angle, providing a crucial parameter to understand the aircraft's stability and controllability during flight. Vertical Tail Angle of Attack is denoted by α_v symbol.

How to calculate Vertical Tail Angle of Attack using this online calculator? To use this online calculator for Vertical Tail Angle of Attack, enter Sidewash Angle (σ) & Sideslip Angle (β) and hit the calculate button. Here is how the Vertical Tail Angle of Attack calculation can be explained with given input values -> 0.117 = 0.067+0.05.

FAQ

What is Vertical Tail Angle of Attack?

Vertical Tail Angle of Attack is a measure of the angle between the vertical tail's aerodynamic force and the aircraft's flight path, calculated by adding the sidewash angle and sideslip angle, providing a crucial parameter to understand the aircraft's stability and controllability during flight and is represented as α_v = σ+β or Vertical Tail Angle of Attack = Sidewash Angle+Sideslip Angle. 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 & 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.

How to calculate Vertical Tail Angle of Attack?

Vertical Tail Angle of Attack is a measure of the angle between the vertical tail's aerodynamic force and the aircraft's flight path, calculated by adding the sidewash angle and sideslip angle, providing a crucial parameter to understand the aircraft's stability and controllability during flight is calculated using Vertical Tail Angle of Attack = Sidewash Angle+Sideslip Angle. To calculate Vertical Tail Angle of Attack, you need Sidewash Angle (σ) & Sideslip Angle (β). With our tool, you need to enter the respective value for Sidewash Angle & Sideslip Angle 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 Angle of Attack?

In this formula, Vertical Tail Angle of Attack uses Sidewash Angle & Sideslip Angle. We can use 1 other way(s) to calculate the same, which is/are as follows -

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

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