Vertical Tail Dynamic Pressure for given Moment Calculator

✖Vertical Tail Moment is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.ⓘ Vertical Tail Moment [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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Vertical Tail Dynamic Pressure for given Moment Solution

STEP 0: Pre-Calculation Summary

Formula Used

Vertical Tail Dynamic Pressure = Vertical Tail Moment/(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.
Vertical Tail Moment - (Measured in Newton Meter) - Vertical Tail Moment 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

Vertical Tail Moment: 5.4 Newton Meter --> 5.4 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) --> 5.4/(1.2*0.7*(0.05+0.067)*5)

Evaluating ... ...

Q_v = 10.989010989011

STEP 3: Convert Result to Output's Unit

10.989010989011 Pascal --> No Conversion Required

FINAL ANSWER

10.989010989011 ≈ 10.98901 Pascal <-- Vertical Tail Dynamic Pressure

(Calculation completed in 00.020 seconds)

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Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

Vinay Mishra has created this Calculator and 300+ more calculators!

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National Institute Of Technology (NIT), Hamirpur

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< Wing Tail Interaction Calculators

Wingspan for Yawing Moment Coefficient given Sideslip Angle and Sidewash Angle

LaTeX 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)

Wing Dynamic Pressure for given Yawing Moment Coefficient

LaTeX Go Wing Dynamic Pressure = Vertical Tail Moment/(Yawing Moment Coefficient*Reference Area*Wingspan)

Wing Area for given Moment Produced by Vertical Tail

LaTeX Go Reference Area = Vertical Tail Moment/(Yawing Moment Coefficient*Wing Dynamic Pressure*Wingspan)

Wingspan for given Yawing Moment Coefficient

LaTeX Go Wingspan = Vertical Tail Moment/(Yawing Moment Coefficient*Reference Area*Wing Dynamic Pressure)

Vertical Tail Dynamic Pressure for given Moment Formula

LaTeX Go

Vertical Tail Dynamic Pressure = Vertical Tail Moment/(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)

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 = Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Area) to calculate the Vertical Tail Dynamic Pressure, Vertical Tail Dynamic Pressure for given Moment is a measure of the pressure exerted by the vertical tail of an aircraft on the surrounding air, calculated by dividing the moment produced by the vertical tail by the product of the vertical tail moment arm, lift curve slope, sideslip angle, sidewash angle, and vertical tail area, providing a critical indicator of aircraft stability and control. 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 Vertical Tail Moment (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 -> 10.98901 = 5.4/(1.2*0.7*(0.05+0.067)*5).

FAQ

What is Vertical Tail Dynamic Pressure for given Moment?

Vertical Tail Dynamic Pressure for given Moment is a measure of the pressure exerted by the vertical tail of an aircraft on the surrounding air, calculated by dividing the moment produced by the vertical tail by the product of the vertical tail moment arm, lift curve slope, sideslip angle, sidewash angle, and vertical tail area, providing a critical indicator of aircraft stability and control and is represented as Q_v = N_v/(𝒍_v*C_v*(β+σ)*S_v) or Vertical Tail Dynamic Pressure = Vertical Tail Moment/(Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Area). Vertical Tail Moment 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?

Vertical Tail Dynamic Pressure for given Moment is a measure of the pressure exerted by the vertical tail of an aircraft on the surrounding air, calculated by dividing the moment produced by the vertical tail by the product of the vertical tail moment arm, lift curve slope, sideslip angle, sidewash angle, and vertical tail area, providing a critical indicator of aircraft stability and control is calculated using Vertical Tail Dynamic Pressure = Vertical Tail Moment/(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 Vertical Tail Moment (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 Vertical Tail Moment, 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 Vertical Tail Moment, 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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