Vertical Tail Lift Curve Slope for Given Moment Calculator

✖Vertical Tail Moment is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.ⓘ Vertical Tail Moment [N_v]			+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 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.ⓘ Vertical Tail Dynamic Pressure [Q_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 for Given Moment [C_v]

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Vertical Tail Lift Curve Slope for Given Moment Solution

STEP 0: Pre-Calculation Summary

Formula Used

Vertical Tail Lift Curve Slope = Vertical Tail Moment/(Vertical Tail Moment Arm*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area)
C_v = N_v/(𝒍_v*(β+σ)*Q_v*S_v)
This formula uses 7 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.
Vertical Tail Moment - (Measured in Newton Meter) - Vertical Tail Moment is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.
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.
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.
Vertical Tail Dynamic Pressure - (Measured in Pascal) - Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an 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.

STEP 1: Convert Input(s) to Base Unit

Vertical Tail Moment: 5.4 Newton Meter --> 5.4 Newton Meter No Conversion Required
Vertical Tail Moment Arm: 1.2 Meter --> 1.2 Meter 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
Vertical Tail Dynamic Pressure: 11 Pascal --> 11 Pascal No Conversion Required
Vertical Tail Area: 5 Square Meter --> 5 Square Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

C_v = N_v/(𝒍_v*(β+σ)*Q_v*S_v) --> 5.4/(1.2*(0.05+0.067)*11*5)

Evaluating ... ...

C_v = 0.699300699300699

STEP 3: Convert Result to Output's Unit

0.699300699300699 1 per Radian --> No Conversion Required

FINAL ANSWER

0.699300699300699 ≈ 0.699301 1 per Radian <-- Vertical Tail Lift Curve Slope

(Calculation completed in 00.007 seconds)

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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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< 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 Moment Formula

LaTeX Go

Vertical Tail Lift Curve Slope = Vertical Tail Moment/(Vertical Tail Moment Arm*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area)
C_v = N_v/(𝒍_v*(β+σ)*Q_v*S_v)

Which device is a secondary flight control?

The secondary flight controls are flaps, trimming devices, spoilers, slats, slots, and speed brakes. The secondary flight controls are not always all present on an aircraft.

How to Calculate Vertical Tail Lift Curve Slope for Given Moment?

Vertical Tail Lift Curve Slope for Given Moment calculator uses Vertical Tail Lift Curve Slope = Vertical Tail Moment/(Vertical Tail Moment Arm*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area) to calculate the Vertical Tail Lift Curve Slope, Vertical Tail Lift Curve Slope for Given Moment is a measure of the rate of change of lift force exerted by the vertical tail of an aircraft in response to sideslip and sidewash angles, which is critical for stability and control during flight, it is a fundamental concept in aerodynamics and aircraft design, helping engineers to optimize the vertical tail's performance and ensure safe and efficient flight operations. Vertical Tail Lift Curve Slope is denoted by C_v symbol.

How to calculate Vertical Tail Lift Curve Slope for Given Moment using this online calculator? To use this online calculator for Vertical Tail Lift Curve Slope for Given Moment, enter Vertical Tail Moment (N_v), Vertical Tail Moment Arm (𝒍_v), Sideslip Angle (β), Sidewash Angle (σ), Vertical Tail Dynamic Pressure (Q_v) & Vertical Tail Area (S_v) and hit the calculate button. Here is how the Vertical Tail Lift Curve Slope for Given Moment calculation can be explained with given input values -> 0.699301 = 5.4/(1.2*(0.05+0.067)*11*5).

FAQ

What is Vertical Tail Lift Curve Slope for Given Moment?

Vertical Tail Lift Curve Slope for Given Moment is a measure of the rate of change of lift force exerted by the vertical tail of an aircraft in response to sideslip and sidewash angles, which is critical for stability and control during flight, it is a fundamental concept in aerodynamics and aircraft design, helping engineers to optimize the vertical tail's performance and ensure safe and efficient flight operations and is represented as C_v = N_v/(𝒍_v*(β+σ)*Q_v*S_v) or 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 Moment is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it, 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 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, Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft & The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline.

How to calculate Vertical Tail Lift Curve Slope for Given Moment?

Vertical Tail Lift Curve Slope for Given Moment is a measure of the rate of change of lift force exerted by the vertical tail of an aircraft in response to sideslip and sidewash angles, which is critical for stability and control during flight, it is a fundamental concept in aerodynamics and aircraft design, helping engineers to optimize the vertical tail's performance and ensure safe and efficient flight operations is calculated using Vertical Tail Lift Curve Slope = Vertical Tail Moment/(Vertical Tail Moment Arm*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area). To calculate Vertical Tail Lift Curve Slope for Given Moment, you need Vertical Tail Moment (N_v), Vertical Tail Moment Arm (𝒍_v), Sideslip Angle (β), Sidewash Angle (σ), Vertical Tail Dynamic Pressure (Q_v) & Vertical Tail Area (S_v). With our tool, you need to enter the respective value for Vertical Tail Moment, Vertical Tail Moment Arm, Sideslip Angle, Sidewash Angle, Vertical Tail Dynamic Pressure & Vertical Tail Area 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 Vertical Tail Moment, Vertical Tail Moment Arm, Sideslip Angle, Sidewash Angle, Vertical Tail Dynamic Pressure & Vertical Tail Area. 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 = Yawing Moment Coefficient/(Vertical Tail Volume Ratio*Vertical Tail Efficiency*(Sideslip Angle+Sidewash Angle))
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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