Vertical tail dynamic pressure 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 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 for given vertical tail side force [Q_v]

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Formula

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Vertical tail dynamic pressure for given vertical tail side force

Formula

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

Example

`"9.203008Pa"=-"-6.12N"/("0.7rad⁻¹"*"0.19rad"*"5m²")`

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Vertical tail dynamic pressure for given vertical tail side force Solution

STEP 0: Pre-Calculation Summary

Formula Used

Vertical tail dynamic pressure = -Vertical Tail Side Force/(Vertical tail Lift curve slope*Vertical tail angle of attack*Vertical tail area)
Q_v = -Y_v/(C_v*α_v*S_v)
This formula uses 5 Variables

Variables Used

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 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.

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 angle of attack: 0.19 Radian --> 0.19 Radian No Conversion Required
Vertical tail area: 5 Square Meter --> 5 Square Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Q_v = -Y_v/(C_v*α_v*S_v) --> -(-6.12)/(0.7*0.19*5)

Evaluating ... ...

Q_v = 9.20300751879699

STEP 3: Convert Result to Output's Unit

9.20300751879699 Pascal --> No Conversion Required

FINAL ANSWER

9.20300751879699 ≈ 9.203008 Pascal <-- Vertical tail dynamic pressure

(Calculation completed in 00.004 seconds)

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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 dynamic pressure for given vertical tail side force Formula

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

What does yaw axis mean?

The yaw axis is defined to be perpendicular to the plane of the wings with its origin at the center of gravity and directed towards the bottom of the aircraft.

How to Calculate Vertical tail dynamic pressure for given vertical tail side force?

Vertical tail dynamic pressure for given vertical tail side force calculator uses Vertical tail dynamic pressure = -Vertical Tail Side Force/(Vertical tail Lift curve slope*Vertical tail angle of attack*Vertical tail area) to calculate the Vertical tail dynamic pressure, The Vertical tail dynamic pressure for given vertical tail side force depends on the vertical tail's lift curve slope, angle of attack, and area. Vertical tail dynamic pressure is denoted by Q_v symbol.

How to calculate Vertical tail dynamic pressure for given vertical tail side force using this online calculator? To use this online calculator for Vertical tail dynamic pressure for given vertical tail side force, enter Vertical Tail Side Force (Y_v), Vertical tail Lift curve slope (C_v), Vertical tail angle of attack (α_v) & Vertical tail area (S_v) and hit the calculate button. Here is how the Vertical tail dynamic pressure for given vertical tail side force calculation can be explained with given input values -> -9.022556 = -(-6.12)/(0.7*0.19*5).

FAQ

What is Vertical tail dynamic pressure for given vertical tail side force?

The Vertical tail dynamic pressure for given vertical tail side force depends on the vertical tail's lift curve slope, angle of attack, and area and is represented as Q_v = -Y_v/(C_v*α_v*S_v) or Vertical tail dynamic pressure = -Vertical Tail Side Force/(Vertical tail Lift curve slope*Vertical tail angle of attack*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 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.

How to calculate Vertical tail dynamic pressure for given vertical tail side force?

The Vertical tail dynamic pressure for given vertical tail side force depends on the vertical tail's lift curve slope, angle of attack, and area is calculated using Vertical tail dynamic pressure = -Vertical Tail Side Force/(Vertical tail Lift curve slope*Vertical tail angle of attack*Vertical tail area). To calculate Vertical tail dynamic pressure for given vertical tail side force, you need Vertical Tail Side Force (Y_v), Vertical tail Lift curve slope (C_v), Vertical tail angle of attack (α_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 angle of attack & Vertical tail area and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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