Vertical Tail Volume Ratio 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%
✖Vertical Tail Efficiency is the tail efficiency associated with the vertical tail of an aircraft.ⓘ Vertical Tail Efficiency [η_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 Volume Ratio relates to the area of the vertical tail, the distance between the centroid of vertical tail area and aircraft's e.g., the wing area, and the wingspan.ⓘ Vertical Tail Volume Ratio for given Yawing Moment Coefficient [V_v]

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Vertical Tail Volume Ratio for given Yawing Moment Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Vertical Tail Volume Ratio = Yawing Moment Coefficient/(Vertical Tail Efficiency*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle))
V_v = C_n/(η_v*C_v*(β+σ))
This formula uses 6 Variables

Variables Used

Vertical Tail Volume Ratio - Vertical Tail Volume Ratio relates to the area of the vertical tail, the distance between the centroid of vertical tail area and aircraft's e.g., the wing area, and the wingspan.
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.
Vertical Tail Efficiency - Vertical Tail Efficiency is the tail efficiency associated with 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.
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
Vertical Tail Efficiency: 16.66 --> 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

V_v = C_n/(η_v*C_v*(β+σ)) --> 1.4/(16.66*0.7*(0.05+0.067))

Evaluating ... ...

V_v = 1.02605144621951

STEP 3: Convert Result to Output's Unit

1.02605144621951 --> No Conversion Required

FINAL ANSWER

1.02605144621951 ≈ 1.026051 <-- Vertical Tail Volume Ratio

(Calculation completed in 00.004 seconds)

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

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< Vertical Tail Contribution Calculators

Vertical Tail Angle of Attack for given Vertical Tail Side Force

LaTeX 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

LaTeX 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

LaTeX Go Vertical Tail Side Force = -Vertical Tail Lift Curve Slope*Vertical Tail Angle of Attack*Vertical Tail Area*Vertical Tail Dynamic Pressure

Vertical Tail Angle of Attack

LaTeX Go Vertical Tail Angle of Attack = Sidewash Angle+Sideslip Angle

Vertical Tail Volume Ratio for given Yawing Moment Coefficient Formula

LaTeX Go

Vertical Tail Volume Ratio = Yawing Moment Coefficient/(Vertical Tail Efficiency*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle))
V_v = C_n/(η_v*C_v*(β+σ))

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How to Calculate Vertical Tail Volume Ratio for given Yawing Moment Coefficient?

Vertical Tail Volume Ratio for given Yawing Moment Coefficient calculator uses Vertical Tail Volume Ratio = Yawing Moment Coefficient/(Vertical Tail Efficiency*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)) to calculate the Vertical Tail Volume Ratio, Vertical Tail Volume Ratio for given Yawing Moment Coefficient is a measure of the proportion of volume required by the vertical tail of an aircraft to counteract the yawing moment, which is influenced by the efficiency of the vertical tail, lift curve slope, sideslip angle, and sidewash angle, this ratio is crucial in aircraft design to ensure stable flight and optimal performance. Vertical Tail Volume Ratio is denoted by V_v symbol.

How to calculate Vertical Tail Volume Ratio for given Yawing Moment Coefficient using this online calculator? To use this online calculator for Vertical Tail Volume Ratio for given Yawing Moment Coefficient, enter Yawing Moment Coefficient (C_n), Vertical Tail Efficiency (η_v), Vertical Tail Lift Curve Slope (C_v), Sideslip Angle (β) & Sidewash Angle (σ) and hit the calculate button. Here is how the Vertical Tail Volume Ratio for given Yawing Moment Coefficient calculation can be explained with given input values -> 1.026051 = 1.4/(16.66*0.7*(0.05+0.067)).

FAQ

What is Vertical Tail Volume Ratio for given Yawing Moment Coefficient?

Vertical Tail Volume Ratio for given Yawing Moment Coefficient is a measure of the proportion of volume required by the vertical tail of an aircraft to counteract the yawing moment, which is influenced by the efficiency of the vertical tail, lift curve slope, sideslip angle, and sidewash angle, this ratio is crucial in aircraft design to ensure stable flight and optimal performance and is represented as V_v = C_n/(η_v*C_v*(β+σ)) or Vertical Tail Volume Ratio = Yawing Moment Coefficient/(Vertical Tail Efficiency*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, Vertical Tail Efficiency is the tail efficiency associated with 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, 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 Vertical Tail Volume Ratio for given Yawing Moment Coefficient?

Vertical Tail Volume Ratio for given Yawing Moment Coefficient is a measure of the proportion of volume required by the vertical tail of an aircraft to counteract the yawing moment, which is influenced by the efficiency of the vertical tail, lift curve slope, sideslip angle, and sidewash angle, this ratio is crucial in aircraft design to ensure stable flight and optimal performance is calculated using Vertical Tail Volume Ratio = Yawing Moment Coefficient/(Vertical Tail Efficiency*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)). To calculate Vertical Tail Volume Ratio for given Yawing Moment Coefficient, you need Yawing Moment Coefficient (C_n), Vertical Tail Efficiency (η_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, Vertical Tail Efficiency, 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 Volume Ratio?

In this formula, Vertical Tail Volume Ratio uses Yawing Moment Coefficient, Vertical Tail Efficiency, Vertical Tail Lift Curve Slope, Sideslip Angle & Sidewash Angle. We can use 1 other way(s) to calculate the same, which is/are as follows -

Vertical Tail Volume Ratio = Vertical Tail Moment Arm*Vertical Tail Area/(Reference Area*Wingspan)

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