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The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft. Check FAQs
Cv=Nv𝒍v⋅(β+σ)⋅Qv⋅Sv
Cv - Vertical Tail Lift Curve Slope?Nv - Vertical Tail Moment?𝒍v - Vertical Tail Moment Arm?β - Sideslip Angle?σ - Sidewash Angle?Qv - Vertical Tail Dynamic Pressure?Sv - Vertical Tail Area?

Vertical Tail Lift Curve Slope for Given Moment Example

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Here is how the Vertical Tail Lift Curve Slope for Given Moment equation looks like with Values.

Here is how the Vertical Tail Lift Curve Slope for Given Moment equation looks like with Units.

Here is how the Vertical Tail Lift Curve Slope for Given Moment equation looks like.

0.6993Edit=5.4Edit1.2Edit⋅(0.05Edit+0.067Edit)⋅11Edit⋅5Edit
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Home » Physics » Aerospace » Aircraft Mechanics » Vertical Tail Lift Curve Slope for Given Moment

Vertical Tail Lift Curve Slope for Given Moment Solution

Follow our step by step solution on how to calculate Vertical Tail Lift Curve Slope for Given Moment?

FIRST Step Consider the formula
Cv=Nv𝒍v⋅(β+σ)⋅Qv⋅Sv
Next Step Substitute values of Variables
∴ Cv=5.4N*m1.2m⋅(0.05rad+0.067rad)⋅11Pa⋅5m²
Next Step Prepare to Evaluate
∴ Cv=5.41.2⋅(0.05+0.067)⋅11⋅5
Next Step Evaluate
∴Cv=0.699300699300699rad⁻¹
LAST Step Rounding Answer
∴Cv=0.6993rad⁻¹

Vertical Tail Lift Curve Slope for Given Moment Formula Elements

Variables
Vertical Tail Lift Curve Slope
The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft.
Symbol: Cv
Measurement: Reciprocal AngleUnit: rad⁻¹
Note: Value can be positive or negative.
Vertical Tail Moment
Vertical Tail Moment is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.
Symbol: Nv
Measurement: Moment of ForceUnit: N*m
Note: Value can be positive or negative.
Vertical Tail Moment Arm
The Vertical Tail Moment Arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft.
Symbol: 𝒍v
Measurement: LengthUnit: m
Note: Value should be greater than 0.
Sideslip Angle
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.
Symbol: β
Measurement: AngleUnit: rad
Note: Value can be positive or negative.
Sidewash Angle
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.
Symbol: σ
Measurement: AngleUnit: rad
Note: Value can be positive or negative.
Vertical Tail Dynamic Pressure
Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft.
Symbol: Qv
Measurement: PressureUnit: Pa
Note: Value should be greater than 0.
Vertical Tail Area
The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline.
Symbol: Sv
Measurement: AreaUnit: m²
Note: Value should be greater than 0.

Credits

Creator Image
Created by Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Formula and 300+ more formulas!
Verifier Image
Verified by Anshika Arya
National Institute Of Technology (NIT), Hamirpur
Anshika Arya has verified this Formula and 2500+ more formulas!

Other Formulas to find Vertical Tail Lift Curve Slope

​Go Vertical Tail Lift Curve Slope
Cv=-(Yvαv⋅Qv⋅Sv)
​Go Vertical Tail Lift Curve Slope for given Vertical Tail Efficiency
Cv=CnVv⋅ηv⋅(β+σ)

Other formulas in Vertical Tail Contribution category

​Go Vertical Tail Angle of Attack
αv=σ+β
​Go Vertical Tail Side Force
Yv=-Cv⋅αv⋅Sv⋅Qv

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

Vertical Tail Lift Curve Slope for Given Moment evaluator 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 evaluate 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 Cv symbol.

How to evaluate Vertical Tail Lift Curve Slope for Given Moment using this online evaluator? To use this online evaluator for Vertical Tail Lift Curve Slope for Given Moment, enter Vertical Tail Moment (Nv), Vertical Tail Moment Arm (𝒍v), Sideslip Angle (β), Sidewash Angle (σ), Vertical Tail Dynamic Pressure (Qv) & Vertical Tail Area (Sv) and hit the calculate button.

FAQs on Vertical Tail Lift Curve Slope for Given Moment

What is the formula to find Vertical Tail Lift Curve Slope for Given Moment?
The formula of Vertical Tail Lift Curve Slope for Given Moment is expressed as Vertical Tail Lift Curve Slope = Vertical Tail Moment/(Vertical Tail Moment Arm*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area). Here is an example- 0.699301 = 5.4/(1.2*(0.05+0.067)*11*5).
How to calculate Vertical Tail Lift Curve Slope for Given Moment?
With Vertical Tail Moment (Nv), Vertical Tail Moment Arm (𝒍v), Sideslip Angle (β), Sidewash Angle (σ), Vertical Tail Dynamic Pressure (Qv) & Vertical Tail Area (Sv) we can find Vertical Tail Lift Curve Slope for Given Moment using the formula - Vertical Tail Lift Curve Slope = Vertical Tail Moment/(Vertical Tail Moment Arm*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area).
What are the other ways to Calculate Vertical Tail Lift Curve Slope?
Here are the different ways to Calculate Vertical Tail Lift Curve Slope-
  • 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))
Can the Vertical Tail Lift Curve Slope for Given Moment be negative?
Yes, the Vertical Tail Lift Curve Slope for Given Moment, measured in Reciprocal Angle can be negative.
Which unit is used to measure Vertical Tail Lift Curve Slope for Given Moment?
Vertical Tail Lift Curve Slope for Given Moment is usually measured using the 1 per Radian[rad⁻¹] for Reciprocal Angle. 1 per Degree[rad⁻¹], 1 per Minute[rad⁻¹], 1 per Quadrant[rad⁻¹] are the few other units in which Vertical Tail Lift Curve Slope for Given Moment can be measured.
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