Vertical tail angle of attack for given vertical tail side force 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

✖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 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 [S_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 for given vertical tail side force [α_v]

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Formula

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Vertical tail angle of attack for given vertical tail side force

Formula

`"α"_{"v"} = -"Y"_{"v"}/("C"_{"v"}*"Q"_{"v"}*"S"_{"v"})`

Example

`"0.158961rad"=-"-6.12N"/("0.7rad⁻¹"*"11Pa"*"5m²")`

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Vertical tail angle of attack for given vertical tail side force Solution

STEP 0: Pre-Calculation Summary

Formula Used

Vertical tail angle of attack = -Vertical Tail Side Force/(Vertical tail Lift curve slope*Vertical tail dynamic pressure*Vertical tail area)
α_v = -Y_v/(C_v*Q_v*S_v)
This formula uses 5 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.
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 dynamic pressure - (Measured in Pascal) - Vertical tail dynamic pressure is the dynamic pressure associated with the vertical tail 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.

STEP 1: Convert Input(s) to Base Unit

Vertical Tail Side Force: -6.12 Newton --> -6.12 Newton No Conversion Required
Vertical tail Lift curve slope: 0.7 1 per Radian --> 0.7 1 per Radian No Conversion Required
Vertical tail dynamic pressure: 11 Pascal --> 11 Pascal No Conversion Required
Vertical tail area: 5 Square Meter --> 5 Square Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

α_v = -Y_v/(C_v*Q_v*S_v) --> -(-6.12)/(0.7*11*5)

Evaluating ... ...

α_v = 0.158961038961039

STEP 3: Convert Result to Output's Unit

0.158961038961039 Radian --> No Conversion Required

FINAL ANSWER

0.158961038961039 ≈ 0.158961 Radian <-- Vertical tail angle of attack

(Calculation completed in 00.004 seconds)

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Home » Physics » Aircraft Mechanics » Static Stability and Control » Directional Stability » Vertical Tail Contribution » Vertical tail angle of attack for given vertical tail side force

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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 angle of attack for given vertical tail side force Formula

Vertical tail angle of attack = -Vertical Tail Side Force/(Vertical tail Lift curve slope*Vertical tail dynamic pressure*Vertical tail area)
α_v = -Y_v/(C_v*Q_v*S_v)

What is a Dutch roll in an aircraft?

A Dutch roll is a combination of rolling and yawing oscillations that occurs when the dihedral effects of an aircraft are more powerful than the directional stability. A Dutch roll is usually dynamically stable but it is an objectionable characteristic in an airplane because of its oscillatory nature.

How to Calculate Vertical tail angle of attack for given vertical tail side force?

Vertical tail angle of attack for given vertical tail side force calculator uses Vertical tail angle of attack = -Vertical Tail Side Force/(Vertical tail Lift curve slope*Vertical tail dynamic pressure*Vertical tail area) to calculate the Vertical tail angle of attack, The Vertical tail angle of attack for given vertical tail side force is the angle between the line of the chord of an aerofoil and the relative airflow. Vertical tail angle of attack is denoted by α_v symbol.

How to calculate Vertical tail angle of attack for given vertical tail side force using this online calculator? To use this online calculator for Vertical tail angle of attack for given vertical tail side force, enter Vertical Tail Side Force (Y_v), Vertical tail Lift curve slope (C_v), Vertical tail dynamic pressure (Q_v) & Vertical tail area (S_v) and hit the calculate button. Here is how the Vertical tail angle of attack for given vertical tail side force calculation can be explained with given input values -> -0.155844 = -(-6.12)/(0.7*11*5).

FAQ

What is Vertical tail angle of attack for given vertical tail side force?

The Vertical tail angle of attack for given vertical tail side force is the angle between the line of the chord of an aerofoil and the relative airflow and is represented as α_v = -Y_v/(C_v*Q_v*S_v) or Vertical tail angle of attack = -Vertical Tail Side Force/(Vertical tail Lift curve slope*Vertical tail dynamic pressure*Vertical tail area). 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 dynamic pressure is the dynamic pressure associated with the vertical tail 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.

How to calculate Vertical tail angle of attack for given vertical tail side force?

The Vertical tail angle of attack for given vertical tail side force is the angle between the line of the chord of an aerofoil and the relative airflow is calculated using Vertical tail angle of attack = -Vertical Tail Side Force/(Vertical tail Lift curve slope*Vertical tail dynamic pressure*Vertical tail area). To calculate Vertical tail angle of attack for given vertical tail side force, you need Vertical Tail Side Force (Y_v), Vertical tail Lift curve slope (C_v), Vertical tail dynamic pressure (Q_v) & Vertical tail area (S_v). With our tool, you need to enter the respective value for Vertical Tail Side Force, Vertical tail Lift curve slope, Vertical tail dynamic pressure & Vertical tail area 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 Vertical Tail Side Force, Vertical tail Lift curve slope, Vertical tail dynamic pressure & Vertical tail area. We can use 1 other way(s) to calculate the same, which is/are as follows -

Vertical tail angle of attack = Sidewash angle+Sideslip angle

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