Vertical Tail Lift Curve Slope for given Vertical Tail Efficiency 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%
✖Vertical Tail Efficiency is the tail efficiency associated with the vertical tail of an aircraft.ⓘ Vertical Tail Efficiency [η_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 Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft.ⓘ Vertical Tail Lift Curve Slope for given Vertical Tail Efficiency [C_v]

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Vertical Tail Lift Curve Slope for given Vertical Tail Efficiency Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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.
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 Efficiency - Vertical Tail Efficiency is the tail efficiency associated with the vertical tail 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 Efficiency: 16.66 --> 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

C_v = C_n/(V_v*η_v*(β+σ)) --> 1.4/(1.02*16.66*(0.05+0.067))

Evaluating ... ...

C_v = 0.704152953287901

STEP 3: Convert Result to Output's Unit

0.704152953287901 1 per Radian --> No Conversion Required

FINAL ANSWER

0.704152953287901 ≈ 0.704153 1 per Radian <-- Vertical Tail Lift Curve Slope

(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 Lift Curve Slope for given Vertical Tail Efficiency Formula

LaTeX Go

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

How is the vertical tail lift curve slope determined?

The vertical tail lift curve slope is determined in the same manner as for the wing and horizontal tail of an aircraft.

How to Calculate Vertical Tail Lift Curve Slope for given Vertical Tail Efficiency?

Vertical Tail Lift Curve Slope for given Vertical Tail Efficiency calculator uses Vertical Tail Lift Curve Slope = Yawing Moment Coefficient/(Vertical Tail Volume Ratio*Vertical Tail Efficiency*(Sideslip Angle+Sidewash Angle)) to calculate the Vertical Tail Lift Curve Slope, Vertical Tail Lift Curve Slope for given Vertical Tail Efficiency is a measure of the rate of change of vertical tail lift with respect to sideslip angle, influenced by the yawing moment coefficient, vertical tail volume ratio, vertical tail efficiency, sideslip angle, and sidewash angle, providing a critical aspect of aircraft stability and control during flight. Vertical Tail Lift Curve Slope is denoted by C_v symbol.

How to calculate Vertical Tail Lift Curve Slope for given Vertical Tail Efficiency using this online calculator? To use this online calculator for Vertical Tail Lift Curve Slope for given Vertical Tail Efficiency, enter Yawing Moment Coefficient (C_n), Vertical Tail Volume Ratio (V_v), Vertical Tail Efficiency (η_v), Sideslip Angle (β) & Sidewash Angle (σ) and hit the calculate button. Here is how the Vertical Tail Lift Curve Slope for given Vertical Tail Efficiency calculation can be explained with given input values -> 0.658932 = 1.4/(1.02*16.66*(0.05+0.067)).

FAQ

What is Vertical Tail Lift Curve Slope for given Vertical Tail Efficiency?

Vertical Tail Lift Curve Slope for given Vertical Tail Efficiency is a measure of the rate of change of vertical tail lift with respect to sideslip angle, influenced by the yawing moment coefficient, vertical tail volume ratio, vertical tail efficiency, sideslip angle, and sidewash angle, providing a critical aspect of aircraft stability and control during flight and is represented as C_v = C_n/(V_v*η_v*(β+σ)) or Vertical Tail Lift Curve Slope = Yawing Moment Coefficient/(Vertical Tail Volume Ratio*Vertical Tail Efficiency*(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, Vertical Tail Efficiency is the tail efficiency associated with the vertical tail 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 Lift Curve Slope for given Vertical Tail Efficiency?

Vertical Tail Lift Curve Slope for given Vertical Tail Efficiency is a measure of the rate of change of vertical tail lift with respect to sideslip angle, influenced by the yawing moment coefficient, vertical tail volume ratio, vertical tail efficiency, sideslip angle, and sidewash angle, providing a critical aspect of aircraft stability and control during flight is calculated using Vertical Tail Lift Curve Slope = Yawing Moment Coefficient/(Vertical Tail Volume Ratio*Vertical Tail Efficiency*(Sideslip Angle+Sidewash Angle)). To calculate Vertical Tail Lift Curve Slope for given Vertical Tail Efficiency, you need Yawing Moment Coefficient (C_n), Vertical Tail Volume Ratio (V_v), Vertical Tail Efficiency (η_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 Efficiency, 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 Lift Curve Slope?

In this formula, Vertical Tail Lift Curve Slope uses Yawing Moment Coefficient, Vertical Tail Volume Ratio, Vertical Tail Efficiency, Sideslip Angle & Sidewash Angle. We can use 3 other way(s) to calculate the same, which is/are as follows -

Vertical Tail Lift Curve Slope = -(Vertical Tail Side Force/(Vertical Tail Angle of Attack*Vertical Tail Dynamic Pressure*Vertical Tail Area))
Vertical Tail Lift Curve Slope = Vertical Tail Moment/(Vertical Tail Moment Arm*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area)
Vertical Tail Lift Curve Slope = Yawing Moment Coefficient*Reference Area*Wingspan*Wing Dynamic Pressure/(Vertical Tail Moment Arm*Vertical Tail Area*Vertical Tail Dynamic Pressure*(Sideslip Angle+Sidewash Angle))

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