Dynamic pressure at wing for given 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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Wing-Tail Interaction

Aerodynamic Parameters

Vertical Tail Contribution

✖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 efficiency is the tail efficiency associated with the vertical tail of an aircraft.ⓘ Vertical tail efficiency [η_v]			+10% -10%

✖Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft.ⓘ Dynamic pressure at wing for given vertical tail efficiency [Q_w]

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Formula

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Dynamic pressure at wing for given vertical tail efficiency

Formula

`"Q"_{"w"} = "Q"_{"v"}/"η"_{"v"}`

Example

`"18.33333Pa"="11Pa"/"0.6"`

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Dynamic pressure at wing for given vertical tail efficiency Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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

STEP 1: Convert Input(s) to Base Unit

Vertical tail dynamic pressure: 11 Pascal --> 11 Pascal No Conversion Required
Vertical tail efficiency: 0.6 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Q_w = Q_v/η_v --> 11/0.6

Evaluating ... ...

Q_w = 18.3333333333333

STEP 3: Convert Result to Output's Unit

18.3333333333333 Pascal --> No Conversion Required

FINAL ANSWER

18.3333333333333 ≈ 18.33333 Pascal <-- Wing dynamic pressure

(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!

< 13 Wing-Tail Interaction Calculators

Sideslip angle for given yawing moment coefficient

Go Sideslip angle = (Yawing moment coefficient/(Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope/(Reference Area*Wingspan*Wing dynamic pressure)))-Sidewash angle

Wingspan for yawing moment coefficient given sideslip angle and sidewash angle

Go Wingspan = Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)/(Reference Area*Yawing moment coefficient*Wing dynamic pressure)

Dynamic pressure at vertical tail for given yawing moment coefficient

Go Vertical tail dynamic pressure = Yawing moment coefficient*Reference Area*Wingspan*Wing dynamic pressure/(Vertical tail moment arm*Vertical tail area*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle))

Dynamic pressure at wing for given yawing moment coefficient

Go Wing dynamic pressure = Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)/(Reference Area*Wingspan*Yawing moment coefficient)

Wing area for given yawing moment coefficient

Go Reference Area = Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)/(Yawing moment coefficient*Wingspan*Wing dynamic pressure)

Vertical tail dynamic pressure for given moment

Go Vertical tail dynamic pressure = Moment produced by vertical tail/(Vertical tail moment arm*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)*Vertical tail area)

Wing dynamic pressure for given yawing moment coefficient

Go Wing dynamic pressure = Moment produced by vertical tail/(Yawing moment coefficient*Reference Area*Wingspan)

Wing area for given moment produced by vertical tail

Go Reference Area = Moment produced by vertical tail/(Yawing moment coefficient*Wing dynamic pressure*Wingspan)

Wingspan for given yawing moment coefficient

Go Wingspan = Moment produced by vertical tail/(Yawing moment coefficient*Reference Area*Wing dynamic pressure)

Wing area for given vertical tail volume ratio

Go Reference Area = Vertical tail moment arm*Vertical tail area/(Wingspan*Vertical Tail Volume Ratio)

Wingspan for given vertical tail volume ratio

Go Wingspan = Vertical tail moment arm*Vertical tail area/(Reference Area*Vertical Tail Volume Ratio)

Dynamic pressure at vertical tail for given vertical tail efficiency

Go Vertical tail dynamic pressure = Vertical tail efficiency*Wing dynamic pressure

Dynamic pressure at wing for given vertical tail efficiency

Go Wing dynamic pressure = Vertical tail dynamic pressure/Vertical tail efficiency

Dynamic pressure at wing for given vertical tail efficiency Formula

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

Can a plane fly without a tail?

A tailless aircraft has no tail assembly and no other horizontal surface besides its main wing. The aerodynamic control and stabilization functions in both pitch and roll are incorporated into the main wing. A tailless type may still have a conventional vertical fin (vertical stabilizer) and rudder.

How to Calculate Dynamic pressure at wing for given vertical tail efficiency?

Dynamic pressure at wing for given vertical tail efficiency calculator uses Wing dynamic pressure = Vertical tail dynamic pressure/Vertical tail efficiency to calculate the Wing dynamic pressure, The Dynamic pressure at wing for given vertical tail efficiency depends on the vertical tail's dynamic pressure. Wing dynamic pressure is denoted by Q_w symbol.

How to calculate Dynamic pressure at wing for given vertical tail efficiency using this online calculator? To use this online calculator for Dynamic pressure at wing for given vertical tail efficiency, enter Vertical tail dynamic pressure (Q_v) & Vertical tail efficiency (η_v) and hit the calculate button. Here is how the Dynamic pressure at wing for given vertical tail efficiency calculation can be explained with given input values -> 18.33333 = 11/0.6.

FAQ

What is Dynamic pressure at wing for given vertical tail efficiency?

The Dynamic pressure at wing for given vertical tail efficiency depends on the vertical tail's dynamic pressure and is represented as Q_w = Q_v/η_v or Wing dynamic pressure = Vertical tail dynamic pressure/Vertical tail efficiency. Vertical tail dynamic pressure is the dynamic pressure associated with the vertical tail of an aircraft & Vertical tail efficiency is the tail efficiency associated with the vertical tail of an aircraft.

How to calculate Dynamic pressure at wing for given vertical tail efficiency?

The Dynamic pressure at wing for given vertical tail efficiency depends on the vertical tail's dynamic pressure is calculated using Wing dynamic pressure = Vertical tail dynamic pressure/Vertical tail efficiency. To calculate Dynamic pressure at wing for given vertical tail efficiency, you need Vertical tail dynamic pressure (Q_v) & Vertical tail efficiency (η_v). With our tool, you need to enter the respective value for Vertical tail dynamic pressure & Vertical tail efficiency 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 Wing dynamic pressure?

In this formula, Wing dynamic pressure uses Vertical tail dynamic pressure & Vertical tail efficiency. We can use 2 other way(s) to calculate the same, which is/are as follows -

Wing dynamic pressure = Moment produced by vertical tail/(Yawing moment coefficient*Reference Area*Wingspan)
Wing dynamic pressure = Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)/(Reference Area*Wingspan*Yawing moment coefficient)

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