Dynamic pressure at vertical tail for given yawing moment coefficient 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

✖Yawing moment coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis.ⓘ Yawing moment coefficient [C_n]			+10% -10%
✖The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.ⓘ Reference Area [S]			+10% -10%
✖The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.ⓘ Wingspan [b]			+10% -10%
✖Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft.ⓘ Wing dynamic pressure [Q_w]			+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 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%
✖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%

✖Vertical tail dynamic pressure is the dynamic pressure associated with the vertical tail of an aircraft.ⓘ Dynamic pressure at vertical tail for given yawing moment coefficient [Q_v]

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Formula

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Dynamic pressure at vertical tail for given yawing moment coefficient

Formula

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

Example

`"477.6068Pa"="1.4"*"5.08m²"*"50m"*"0.66Pa"/("1.2m"*"5m²"*"0.7rad⁻¹"*("0.05rad"+"0.067rad"))`

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Dynamic pressure at vertical tail for given yawing moment coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

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))
Q_v = C_n*S*b*Q_w/(𝒍_v*S_v*C_v*(β+σ))
This formula uses 10 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.
Yawing moment coefficient - Yawing moment coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis.
Reference Area - (Measured in Square Meter) - The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.
Wingspan - (Measured in Meter) - The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.
Wing dynamic pressure - (Measured in Pascal) - Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft.
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 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.
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.

STEP 1: Convert Input(s) to Base Unit

Yawing moment coefficient: 1.4 --> No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Wingspan: 50 Meter --> 50 Meter No Conversion Required
Wing dynamic pressure: 0.66 Pascal --> 0.66 Pascal No Conversion Required
Vertical tail moment arm: 1.2 Meter --> 1.2 Meter No Conversion Required
Vertical tail area: 5 Square Meter --> 5 Square 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

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Q_v = C_n*S*b*Q_w/(𝒍_v*S_v*C_v*(β+σ)) --> 1.4*5.08*50*0.66/(1.2*5*0.7*(0.05+0.067))

Evaluating ... ...

Q_v = 477.606837606838

STEP 3: Convert Result to Output's Unit

477.606837606838 Pascal --> No Conversion Required

FINAL ANSWER

477.606837606838 ≈ 477.6068 Pascal <-- Vertical tail dynamic pressure

(Calculation completed in 00.020 seconds)

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Home » Physics » Aircraft Mechanics » Static Stability and Control » Directional Stability » Wing-Tail Interaction » Dynamic pressure at vertical tail for given yawing moment coefficient

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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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< 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 vertical tail for given yawing moment coefficient Formula

What causes dynamic pressure?

The dynamic pressure is caused by kinetic energy. The sum of static and dynamic pressure is the total pressure. It is measured by a Pitot tube.

How to Calculate Dynamic pressure at vertical tail for given yawing moment coefficient?

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

How to calculate Dynamic pressure at vertical tail for given yawing moment coefficient using this online calculator? To use this online calculator for Dynamic pressure at vertical tail for given yawing moment coefficient, enter Yawing moment coefficient (C_n), Reference Area (S), Wingspan (b), Wing dynamic pressure (Q_w), Vertical tail moment arm (𝒍_v), Vertical tail area (S_v), Vertical tail Lift curve slope (C_v), Sideslip angle (β) & Sidewash angle (σ) and hit the calculate button. Here is how the Dynamic pressure at vertical tail for given yawing moment coefficient calculation can be explained with given input values -> 477.6068 = 1.4*5.08*50*0.66/(1.2*5*0.7*(0.05+0.067)).

FAQ

What is Dynamic pressure at vertical tail for given yawing moment coefficient?

The Dynamic pressure at vertical tail for given yawing moment coefficient is a function of the vertical tail's moment arm, area, lift curve slope, sideslip angle, sidewash angle, wing's reference area, wingspan, and dynamic pressure at wing and is represented as Q_v = C_n*S*b*Q_w/(𝒍_v*S_v*C_v*(β+σ)) or 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)). Yawing moment coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis, The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area, The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip, Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft, 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 area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline, 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.

How to calculate Dynamic pressure at vertical tail for given yawing moment coefficient?

The Dynamic pressure at vertical tail for given yawing moment coefficient is a function of the vertical tail's moment arm, area, lift curve slope, sideslip angle, sidewash angle, wing's reference area, wingspan, and dynamic pressure at wing is calculated using 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)). To calculate Dynamic pressure at vertical tail for given yawing moment coefficient, you need Yawing moment coefficient (C_n), Reference Area (S), Wingspan (b), Wing dynamic pressure (Q_w), Vertical tail moment arm (𝒍_v), Vertical tail area (S_v), Vertical tail Lift curve slope (C_v), Sideslip angle (β) & Sidewash angle (σ). With our tool, you need to enter the respective value for 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 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 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. We can use 2 other way(s) to calculate the same, which is/are as follows -

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

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