Vertical tail efficiency 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 dynamic pressure is the dynamic pressure associated with the vertical tail of an aircraft.ⓘ Vertical tail dynamic pressure [Q_v]			+10% -10%
✖Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft.ⓘ Wing dynamic pressure [Q_w]			+10% -10%

✖Vertical tail efficiency is the tail efficiency associated with the vertical tail of an aircraft.ⓘ Vertical tail efficiency [η_v]

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Formula

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Vertical tail efficiency

Formula

`"η"_{"v"} = "Q"_{"v"}/"Q"_{"w"}`

Example

`"16.66667"="11Pa"/"0.66Pa"`

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Vertical tail efficiency Solution

STEP 0: Pre-Calculation Summary

Formula Used

Vertical tail efficiency = Vertical tail dynamic pressure/Wing dynamic pressure
η_v = Q_v/Q_w
This formula uses 3 Variables

Variables Used

Vertical tail efficiency - Vertical tail efficiency is the tail efficiency associated with the vertical tail 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.
Wing dynamic pressure - (Measured in Pascal) - Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft.

STEP 1: Convert Input(s) to Base Unit

Vertical tail dynamic pressure: 11 Pascal --> 11 Pascal No Conversion Required
Wing dynamic pressure: 0.66 Pascal --> 0.66 Pascal No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

η_v = Q_v/Q_w --> 11/0.66

Evaluating ... ...

η_v = 16.6666666666667

STEP 3: Convert Result to Output's Unit

16.6666666666667 --> No Conversion Required

FINAL ANSWER

16.6666666666667 ≈ 16.66667 <-- Vertical tail efficiency

(Calculation completed in 00.004 seconds)

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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 Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

Sanjay Krishna has verified this Calculator and 200+ more calculators!

< 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 efficiency Formula

Vertical tail efficiency = Vertical tail dynamic pressure/Wing dynamic pressure
η_v = Q_v/Q_w

How does a tailplane work?

The function of the tailplane is to provide stability and control. In particular, the tailplane helps adjust for changes in position of the centre of pressure or centre of gravity caused by changes in speed and attitude, fuel consumption, or dropping cargo or payload.

How to Calculate Vertical tail efficiency?

Vertical tail efficiency calculator uses Vertical tail efficiency = Vertical tail dynamic pressure/Wing dynamic pressure to calculate the Vertical tail efficiency, The Vertical tail efficiency of an aircraft is the ratio of dynamic pressure at the vertical tail to the dynamic pressure at the wing. Vertical tail efficiency is denoted by η_v symbol.

How to calculate Vertical tail efficiency using this online calculator? To use this online calculator for Vertical tail efficiency, enter Vertical tail dynamic pressure (Q_v) & Wing dynamic pressure (Q_w) and hit the calculate button. Here is how the Vertical tail efficiency calculation can be explained with given input values -> 16.66667 = 11/0.66.

FAQ

What is Vertical tail efficiency?

The Vertical tail efficiency of an aircraft is the ratio of dynamic pressure at the vertical tail to the dynamic pressure at the wing and is represented as η_v = Q_v/Q_w or Vertical tail efficiency = Vertical tail dynamic pressure/Wing dynamic pressure. Vertical tail dynamic pressure is the dynamic pressure associated with the vertical tail of an aircraft & Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft.

How to calculate Vertical tail efficiency?

The Vertical tail efficiency of an aircraft is the ratio of dynamic pressure at the vertical tail to the dynamic pressure at the wing is calculated using Vertical tail efficiency = Vertical tail dynamic pressure/Wing dynamic pressure. To calculate Vertical tail efficiency, you need Vertical tail dynamic pressure (Q_v) & Wing dynamic pressure (Q_w). With our tool, you need to enter the respective value for Vertical tail dynamic pressure & Wing 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 efficiency?

In this formula, Vertical tail efficiency uses Vertical tail dynamic pressure & Wing dynamic pressure. We can use 1 other way(s) to calculate the same, which is/are as follows -

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

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