Vertical Tail Angle of Attack for given Vertical Tail Side Force 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%
✖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%
✖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%

✖Vertical Tail Angle of Attack is the angle of attack experienced by the vertical tailplane of an aircraft.ⓘ Vertical Tail Angle of Attack for given Vertical Tail Side Force [α_v]

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Vertical Tail Angle of Attack for given Vertical Tail Side Force Solution

STEP 0: Pre-Calculation Summary

Formula Used

Vertical Tail Angle of Attack = -(Vertical Tail Side Force/(Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area))
α_v = -(Y_v/(C_v*Q_v*S_v))
This formula uses 5 Variables

Variables Used

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 Side Force - (Measured in Newton) - Vertical Tail Side Force is the side force acting on the vertical tail of an aircraft.
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 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 Lift Curve Slope: 0.7 1 per Radian --> 0.7 1 per 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

α_v = -(Y_v/(C_v*Q_v*S_v)) --> -((-4.235)/(0.7*11*5))

Evaluating ... ...

α_v = 0.11

STEP 3: Convert Result to Output's Unit

0.11 Radian --> No Conversion Required

FINAL ANSWER

0.11 Radian <-- Vertical Tail Angle of Attack

(Calculation completed in 00.004 seconds)

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Created by Vinay Mishra

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 Angle of Attack for given Vertical Tail Side Force Formula

LaTeX Go

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

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How to Calculate Vertical Tail Angle of Attack for given Vertical Tail Side Force?

Vertical Tail Angle of Attack for given Vertical Tail Side Force calculator uses Vertical Tail Angle of Attack = -(Vertical Tail Side Force/(Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area)) to calculate the Vertical Tail Angle of Attack, Vertical Tail Angle of Attack for given Vertical Tail Side Force is a measure of the angle at which the vertical tail of an aircraft meets the oncoming airflow, calculated by dividing the vertical tail side force by the product of the vertical tail lift curve slope, dynamic pressure, and area. This angle is critical in determining the stability and control of the aircraft during flight and is essential for ensuring safe and efficient flight operations. Vertical Tail Angle of Attack is denoted by α_v symbol.

How to calculate Vertical Tail Angle of Attack for given Vertical Tail Side Force using this online calculator? To use this online calculator for Vertical Tail Angle of Attack for given Vertical Tail Side Force, enter Vertical Tail Side Force (Y_v), Vertical Tail Lift Curve Slope (C_v), Vertical Tail Dynamic Pressure (Q_v) & Vertical Tail Area (S_v) and hit the calculate button. Here is how the Vertical Tail Angle of Attack for given Vertical Tail Side Force calculation can be explained with given input values -> 0.11 = -((-4.235)/(0.7*11*5)).

FAQ

What is Vertical Tail Angle of Attack for given Vertical Tail Side Force?

Vertical Tail Angle of Attack for given Vertical Tail Side Force is a measure of the angle at which the vertical tail of an aircraft meets the oncoming airflow, calculated by dividing the vertical tail side force by the product of the vertical tail lift curve slope, dynamic pressure, and area. This angle is critical in determining the stability and control of the aircraft during flight and is essential for ensuring safe and efficient flight operations and is represented as α_v = -(Y_v/(C_v*Q_v*S_v)) or Vertical Tail Angle of Attack = -(Vertical Tail Side Force/(Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area)). Vertical Tail Side Force is the side force acting on the vertical tail of an aircraft, The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a 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 Angle of Attack for given Vertical Tail Side Force?

Vertical Tail Angle of Attack for given Vertical Tail Side Force is a measure of the angle at which the vertical tail of an aircraft meets the oncoming airflow, calculated by dividing the vertical tail side force by the product of the vertical tail lift curve slope, dynamic pressure, and area. This angle is critical in determining the stability and control of the aircraft during flight and is essential for ensuring safe and efficient flight operations is calculated using Vertical Tail Angle of Attack = -(Vertical Tail Side Force/(Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area)). To calculate Vertical Tail Angle of Attack for given Vertical Tail Side Force, you need Vertical Tail Side Force (Y_v), Vertical Tail Lift Curve Slope (C_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 Lift Curve Slope, 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 Angle of Attack?

In this formula, Vertical Tail Angle of Attack uses Vertical Tail Side Force, Vertical Tail Lift Curve Slope, Vertical Tail Dynamic Pressure & Vertical Tail Area. We can use 1 other way(s) to calculate the same, which is/are as follows -

Vertical Tail Angle of Attack = Sidewash Angle+Sideslip Angle

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