Vertical Tail Efficiency 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 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 [V_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 Efficiency is the tail efficiency associated with the vertical tail of an aircraft.ⓘ Vertical Tail Efficiency for given Yawing Moment Coefficient [η_v]

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Vertical Tail Efficiency for given Yawing Moment Coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

Vertical Tail Efficiency - Vertical Tail Efficiency is the tail efficiency 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.
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.
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 Volume Ratio: 1.02 --> 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

η_v = C_n/(V_v*C_v*(β+σ)) --> 1.4/(1.02*0.7*(0.05+0.067))

Evaluating ... ...

η_v = 16.7588402882521

STEP 3: Convert Result to Output's Unit

16.7588402882521 --> No Conversion Required

FINAL ANSWER

16.7588402882521 ≈ 16.75884 <-- Vertical Tail Efficiency

(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 Efficiency for given Yawing Moment Coefficient Formula

LaTeX Go

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

What does the tail efficiency factor depend on?

The tail efficiency factor depends on the tail location with respect to the airplane wake and slipstream of the engine and power effects.

How to Calculate Vertical Tail Efficiency for given Yawing Moment Coefficient?

Vertical Tail Efficiency for given Yawing Moment Coefficient calculator uses Vertical Tail Efficiency = Yawing Moment Coefficient/(Vertical Tail Volume Ratio*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)) to calculate the Vertical Tail Efficiency, Vertical Tail Efficiency for given Yawing Moment Coefficient is a measure of the effectiveness of a vertical tail in generating yawing moment, taking into account the yawing moment coefficient, vertical tail volume ratio, lift curve slope, sideslip angle, and sidewash angle, providing a critical assessment of an aircraft's directional stability and control. Vertical Tail Efficiency is denoted by η_v symbol.

How to calculate Vertical Tail Efficiency for given Yawing Moment Coefficient using this online calculator? To use this online calculator for Vertical Tail Efficiency for given Yawing Moment Coefficient, enter Yawing Moment Coefficient (C_n), Vertical Tail Volume Ratio (V_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 Efficiency for given Yawing Moment Coefficient calculation can be explained with given input values -> 15.68258 = 1.4/(1.02*0.7*(0.05+0.067)).

FAQ

What is Vertical Tail Efficiency for given Yawing Moment Coefficient?

Vertical Tail Efficiency for given Yawing Moment Coefficient is a measure of the effectiveness of a vertical tail in generating yawing moment, taking into account the yawing moment coefficient, vertical tail volume ratio, lift curve slope, sideslip angle, and sidewash angle, providing a critical assessment of an aircraft's directional stability and control and is represented as η_v = C_n/(V_v*C_v*(β+σ)) or Vertical Tail Efficiency = Yawing Moment Coefficient/(Vertical Tail Volume Ratio*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 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, 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 Efficiency for given Yawing Moment Coefficient?

Vertical Tail Efficiency for given Yawing Moment Coefficient is a measure of the effectiveness of a vertical tail in generating yawing moment, taking into account the yawing moment coefficient, vertical tail volume ratio, lift curve slope, sideslip angle, and sidewash angle, providing a critical assessment of an aircraft's directional stability and control is calculated using Vertical Tail Efficiency = Yawing Moment Coefficient/(Vertical Tail Volume Ratio*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)). To calculate Vertical Tail Efficiency for given Yawing Moment Coefficient, you need Yawing Moment Coefficient (C_n), Vertical Tail Volume Ratio (V_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 Volume Ratio, 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 Efficiency?

In this formula, Vertical Tail Efficiency uses Yawing Moment Coefficient, Vertical Tail Volume Ratio, 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 Efficiency = Vertical Tail Dynamic Pressure/Wing Dynamic Pressure

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