Vertical Tail Lift Curve Slope Calculator

✖Vertical Tail Side Force is the side force acting on the vertical tail of an aircraft.ⓘ Vertical Tail Side Force [Y_v]			+10% -10%
✖Vertical Tail Angle of Attack is the angle of attack experienced by the vertical tailplane of an aircraft.ⓘ Vertical Tail Angle of Attack [α_v]			+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 [C_v]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Vertical Tail Contribution Formulas PDF PDF Image

Vertical Tail Lift Curve Slope Solution

STEP 0: Pre-Calculation Summary

Formula Used

Vertical Tail Lift Curve Slope = -(Vertical Tail Side Force/(Vertical Tail Angle of Attack*Vertical Tail Dynamic Pressure*Vertical Tail Area))
C_v = -(Y_v/(α_v*Q_v*S_v))
This formula uses 5 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 Side Force - (Measured in Newton) - Vertical Tail Side Force is the side force acting on the vertical tail of an aircraft.
Vertical Tail Angle of Attack - (Measured in Radian) - Vertical Tail Angle of Attack is the angle of attack experienced by the vertical tailplane of an aircraft.
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 Side Force: -4.235 Newton --> -4.235 Newton No Conversion Required
Vertical Tail Angle of Attack: 0.117 Radian --> 0.117 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 = -(Y_v/(α_v*Q_v*S_v)) --> -((-4.235)/(0.117*11*5))

Evaluating ... ...

C_v = 0.658119658119658

STEP 3: Convert Result to Output's Unit

0.658119658119658 1 per Radian --> No Conversion Required

FINAL ANSWER

0.658119658119658 ≈ 0.65812 1 per Radian <-- Vertical Tail Lift Curve Slope

(Calculation completed in 00.004 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Static Stability and Control » Directional Stability » Aerospace » Vertical Tail Contribution » Vertical Tail Lift Curve Slope

Credits

Created by Vinay Mishra

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

Vinay Mishra has created this Calculator and 300+ more calculators!

Verified by Anshika Arya

National Institute Of Technology (NIT), Hamirpur

Anshika Arya has verified this Calculator and 2500+ more calculators!

< 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 Formula

LaTeX Go

Vertical Tail Lift Curve Slope = -(Vertical Tail Side Force/(Vertical Tail Angle of Attack*Vertical Tail Dynamic Pressure*Vertical Tail Area))
C_v = -(Y_v/(α_v*Q_v*S_v))

Which is the minimum requirement for pure directional stability?

An aircraft is said to be in pure directional stability if the yawing moment curve slope is positive.

How to Calculate Vertical Tail Lift Curve Slope?

Vertical Tail Lift Curve Slope calculator uses Vertical Tail Lift Curve Slope = -(Vertical Tail Side Force/(Vertical Tail Angle of Attack*Vertical Tail Dynamic Pressure*Vertical Tail Area)) to calculate the Vertical Tail Lift Curve Slope, Vertical Tail Lift Curve Slope is a measure of the rate of change of vertical tail lift with respect to the angle of attack, which is essential in analyzing the stability and control of an aircraft during flight and is calculated by dividing the vertical tail side force by the product of the vertical tail angle of attack, dynamic pressure, and vertical tail area. Vertical Tail Lift Curve Slope is denoted by C_v symbol.

How to calculate Vertical Tail Lift Curve Slope using this online calculator? To use this online calculator for Vertical Tail Lift Curve Slope, enter Vertical Tail Side Force (Y_v), Vertical Tail Angle of Attack (α_v), 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 calculation can be explained with given input values -> 0.65812 = -((-4.235)/(0.117*11*5)).

FAQ

What is Vertical Tail Lift Curve Slope?

Vertical Tail Lift Curve Slope is a measure of the rate of change of vertical tail lift with respect to the angle of attack, which is essential in analyzing the stability and control of an aircraft during flight and is calculated by dividing the vertical tail side force by the product of the vertical tail angle of attack, dynamic pressure, and vertical tail area and is represented as C_v = -(Y_v/(α_v*Q_v*S_v)) or 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 is the side force acting on the vertical tail of an aircraft, Vertical Tail Angle of Attack is the angle of attack experienced by the vertical tailplane of an aircraft, 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?

Vertical Tail Lift Curve Slope is a measure of the rate of change of vertical tail lift with respect to the angle of attack, which is essential in analyzing the stability and control of an aircraft during flight and is calculated by dividing the vertical tail side force by the product of the vertical tail angle of attack, dynamic pressure, and vertical tail area is calculated using Vertical Tail Lift Curve Slope = -(Vertical Tail Side Force/(Vertical Tail Angle of Attack*Vertical Tail Dynamic Pressure*Vertical Tail Area)). To calculate Vertical Tail Lift Curve Slope, you need Vertical Tail Side Force (Y_v), Vertical Tail Angle of Attack (α_v), Vertical Tail Dynamic Pressure (Q_v) & Vertical Tail Area (S_v). With our tool, you need to enter the respective value for Vertical Tail Side Force, Vertical Tail Angle of Attack, 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 Side Force, Vertical Tail Angle of Attack, 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 Moment/(Vertical Tail Moment Arm*(Sideslip Angle+Sidewash Angle)*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))

Home

FREE PDFs

🔍 Search