Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient Calculator

✖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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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: 1.15 Meter --> 1.15 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*1.15*0.66/(1.2*5*0.7*(0.05+0.067))

Evaluating ... ...

Q_v = 10.9849572649573

STEP 3: Convert Result to Output's Unit

10.9849572649573 Pascal --> No Conversion Required

FINAL ANSWER

10.9849572649573 ≈ 10.98496 Pascal <-- Vertical Tail Dynamic Pressure

(Calculation completed in 00.023 seconds)

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

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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)

Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient Formula

LaTeX Go

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, Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient is a measure of the pressure exerted on the vertical tail of an aircraft, influenced by the yawing moment coefficient, reference area, wingspan, wing dynamic pressure and other factors, which affects the stability and control of the aircraft during flight. 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 -> 10.98496 = 1.4*5.08*1.15*0.66/(1.2*5*0.7*(0.05+0.067)).

FAQ

What is Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient?

Dynamic Pressure at Vertical Tail for given Yawing Moment Coefficient is a measure of the pressure exerted on the vertical tail of an aircraft, influenced by the yawing moment coefficient, reference area, wingspan, wing dynamic pressure and other factors, which affects the stability and control of the aircraft during flight 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?

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 = Vertical Tail Moment/(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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