Vertical tail dynamic pressure for given moment Calculator

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Static Stability and Control

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Vertical Tail Contribution

✖The moment produced by vertical tail is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.ⓘ Moment produced by vertical tail [N_v]			+10% -10%
✖The vertical tail moment arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft.ⓘ Vertical tail moment arm [𝒍_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%
✖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%
✖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 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 moment [Q_v]

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Formula

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Vertical tail dynamic pressure for given moment

Formula

`"Q"_{"v"} = "N"_{"v"}/("𝒍"_{"v"}*"C"_{"v"}*("β"+"σ")*"S"_{"v"})`

Example

`"4.070004Pa"="2N*m"/("1.2m"*"0.7rad⁻¹"*("0.05rad"+"0.067rad")*"5m²")`

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Vertical tail dynamic pressure for given moment Solution

STEP 0: Pre-Calculation Summary

Formula Used

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)
Q_v = N_v/(𝒍_v*C_v*(β+σ)*S_v)
This formula uses 7 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.
Moment produced by vertical tail - (Measured in Newton Meter) - The moment produced by vertical tail is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.
Vertical tail moment arm - (Measured in Meter) - The vertical tail moment arm is the distance between the centroid of the vertical tail shape and the center of gravity of the 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.
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.
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.
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

Moment produced by vertical tail: 2 Newton Meter --> 2 Newton Meter No Conversion Required
Vertical tail moment arm: 1.2 Meter --> 1.2 Meter No Conversion Required
Vertical tail Lift curve slope: 0.7 1 per Radian --> 0.7 1 per Radian No Conversion Required
Sideslip angle: 0.05 Radian --> 0.05 Radian No Conversion Required
Sidewash angle: 0.067 Radian --> 0.067 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 = N_v/(𝒍_v*C_v*(β+σ)*S_v) --> 2/(1.2*0.7*(0.05+0.067)*5)

Evaluating ... ...

Q_v = 4.07000407000407

STEP 3: Convert Result to Output's Unit

4.07000407000407 Pascal --> No Conversion Required

FINAL ANSWER

4.07000407000407 ≈ 4.070004 Pascal <-- Vertical tail 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 Anshika Arya

National Institute Of Technology (NIT), Hamirpur

Anshika Arya has verified this Calculator and 2500+ 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

Vertical tail dynamic pressure for given moment Formula

What is dynamic pressure in aviation?

The dynamic pressure is the excess pressure above ambient that develops when air is compressed and adiabatically brought to rest relative to the moving aircraft.

How to Calculate Vertical tail dynamic pressure for given moment?

Vertical tail dynamic pressure for given moment calculator uses 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) to calculate the Vertical tail dynamic pressure, The Vertical tail dynamic pressure for given moment produced by the vertical tail is a function of the vertical tail's moment arm, lift curve slope, sideslip angle, sidewash angle, and area. Vertical tail dynamic pressure is denoted by Q_v symbol.

How to calculate Vertical tail dynamic pressure for given moment using this online calculator? To use this online calculator for Vertical tail dynamic pressure for given moment, enter Moment produced by vertical tail (N_v), Vertical tail moment arm (𝒍_v), Vertical tail Lift curve slope (C_v), Sideslip angle (β), Sidewash angle (σ) & Vertical tail area (S_v) and hit the calculate button. Here is how the Vertical tail dynamic pressure for given moment calculation can be explained with given input values -> 4.070004 = 2/(1.2*0.7*(0.05+0.067)*5).

FAQ

What is Vertical tail dynamic pressure for given moment?

The Vertical tail dynamic pressure for given moment produced by the vertical tail is a function of the vertical tail's moment arm, lift curve slope, sideslip angle, sidewash angle, and area and is represented as Q_v = N_v/(𝒍_v*C_v*(β+σ)*S_v) or 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). The moment produced by vertical tail is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it, The vertical tail moment arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft, The Vertical tail Lift curve slope is the slope associated with the lift curve of a vertical tailplane of an aircraft, 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, 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 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 moment?

The Vertical tail dynamic pressure for given moment produced by the vertical tail is a function of the vertical tail's moment arm, lift curve slope, sideslip angle, sidewash angle, and area is calculated using 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). To calculate Vertical tail dynamic pressure for given moment, you need Moment produced by vertical tail (N_v), Vertical tail moment arm (𝒍_v), Vertical tail Lift curve slope (C_v), Sideslip angle (β), Sidewash angle (σ) & Vertical tail area (S_v). With our tool, you need to enter the respective value for Moment produced by vertical tail, Vertical tail moment arm, Vertical tail Lift curve slope, Sideslip angle, Sidewash angle & 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 dynamic pressure?

In this formula, Vertical tail dynamic pressure uses Moment produced by vertical tail, Vertical tail moment arm, Vertical tail Lift curve slope, Sideslip angle, Sidewash angle & Vertical tail area. We can use 2 other way(s) to calculate the same, which is/are as follows -

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

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