Vertical Tail Dynamic Pressure 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 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%
✖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 Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft.ⓘ Vertical Tail Dynamic Pressure for given Vertical Tail Side Force [Q_v]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Vertical Tail Contribution Formulas PDF PDF Image

Vertical Tail Dynamic Pressure for given Vertical Tail Side Force Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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 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 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 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 Angle of Attack: 0.117 Radian --> 0.117 Radian No Conversion Required
Vertical Tail Area: 5 Square Meter --> 5 Square Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

Q_v = -(Y_v/(C_v*α_v*S_v)) --> -((-4.235)/(0.7*0.117*5))

Evaluating ... ...

Q_v = 10.3418803418803

STEP 3: Convert Result to Output's Unit

10.3418803418803 Pascal --> No Conversion Required

FINAL ANSWER

10.3418803418803 ≈ 10.34188 Pascal <-- Vertical Tail Dynamic Pressure

(Calculation completed in 00.020 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Static Stability and Control » Directional Stability » Aerospace » Vertical Tail Contribution » Vertical Tail Dynamic Pressure for given Vertical Tail Side Force

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 Dynamic Pressure for given Vertical Tail Side Force Formula

LaTeX Go

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

What does yaw axis mean?

The yaw axis is defined to be perpendicular to the plane of the wings with its origin at the center of gravity and directed towards the bottom of the aircraft.

How to Calculate Vertical Tail Dynamic Pressure for given Vertical Tail Side Force?

Vertical Tail Dynamic Pressure for given Vertical Tail Side Force calculator uses Vertical Tail Dynamic Pressure = -(Vertical Tail Side Force/(Vertical Tail Lift Curve Slope*Vertical Tail Angle of Attack*Vertical Tail Area)) to calculate the Vertical Tail Dynamic Pressure, Vertical tail dynamic pressure for given vertical tail side force is a measure of the pressure exerted by the vertical tail of an aircraft, calculated by dividing the vertical tail side force by the product of the vertical tail lift curve slope, vertical tail angle of attack, and vertical tail area, providing a critical parameter for aircraft stability and control. Vertical Tail Dynamic Pressure is denoted by Q_v symbol.

How to calculate Vertical Tail Dynamic Pressure for given Vertical Tail Side Force using this online calculator? To use this online calculator for Vertical Tail Dynamic Pressure for given Vertical Tail Side Force, enter Vertical Tail Side Force (Y_v), Vertical Tail Lift Curve Slope (C_v), Vertical Tail Angle of Attack (α_v) & Vertical Tail Area (S_v) and hit the calculate button. Here is how the Vertical Tail Dynamic Pressure for given Vertical Tail Side Force calculation can be explained with given input values -> 10.34188 = -((-4.235)/(0.7*0.117*5)).

FAQ

What is Vertical Tail Dynamic Pressure for given Vertical Tail Side Force?

Vertical tail dynamic pressure for given vertical tail side force is a measure of the pressure exerted by the vertical tail of an aircraft, calculated by dividing the vertical tail side force by the product of the vertical tail lift curve slope, vertical tail angle of attack, and vertical tail area, providing a critical parameter for aircraft stability and control and is represented as Q_v = -(Y_v/(C_v*α_v*S_v)) or Vertical Tail Dynamic Pressure = -(Vertical Tail Side Force/(Vertical Tail Lift Curve Slope*Vertical Tail Angle of Attack*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 Angle of Attack is the angle of attack experienced by the vertical tailplane 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 Dynamic Pressure for given Vertical Tail Side Force?

Vertical tail dynamic pressure for given vertical tail side force is a measure of the pressure exerted by the vertical tail of an aircraft, calculated by dividing the vertical tail side force by the product of the vertical tail lift curve slope, vertical tail angle of attack, and vertical tail area, providing a critical parameter for aircraft stability and control is calculated using Vertical Tail Dynamic Pressure = -(Vertical Tail Side Force/(Vertical Tail Lift Curve Slope*Vertical Tail Angle of Attack*Vertical Tail Area)). To calculate Vertical Tail Dynamic Pressure for given Vertical Tail Side Force, you need Vertical Tail Side Force (Y_v), Vertical Tail Lift Curve Slope (C_v), Vertical Tail Angle of Attack (α_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 Angle of Attack & Vertical Tail Area and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

Home

FREE PDFs

🔍 Search