Moment produced by vertical tail for given side force Solution

STEP 0: Pre-Calculation Summary
Formula Used
Moment produced by vertical tail = Vertical tail moment arm*Vertical Tail Side Force
Nv = ๐’v*Yv
This formula uses 3 Variables
Variables Used
Moment produced by vertical tail - (Measured in Newton Meter) - The moment produced by vertical tail 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.
Vertical Tail Side Force - (Measured in Newton) - Vertical Tail Side Force is the side force acting on the vertical tail of an aircraft.
STEP 1: Convert Input(s) to Base Unit
Vertical tail moment arm: 1.2 Meter --> 1.2 Meter No Conversion Required
Vertical Tail Side Force: -6.12 Newton --> -6.12 Newton No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
Nv = ๐’v*Yv --> 1.2*(-6.12)
Evaluating ... ...
Nv = -7.344
STEP 3: Convert Result to Output's Unit
-7.344 Newton Meter --> No Conversion Required
FINAL ANSWER
-7.344 Newton Meter <-- Moment produced by vertical tail
(Calculation completed in 00.004 seconds)

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 Shikha Maurya
Indian Institute of Technology (IIT), Bombay
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24 Vertical Tail Contribution Calculators

Vertical tail moment arm for given yawing moment coefficient
Go Vertical tail moment arm = Yawing moment coefficient/(Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)/(Reference Area*Wingspan*Wing dynamic pressure))
Vertical tail area for given yawing moment coefficient
Go Vertical tail area = Yawing moment coefficient*(Reference Area*Wingspan*Wing dynamic pressure)/(Vertical tail moment arm*Vertical tail dynamic pressure*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle))
Vertical tail lift curve slope for given yawing moment coefficient
Go 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))
Vertical tail moment arm for given lift curve slope
Go Vertical tail moment arm = Moment produced by vertical tail/(Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)*Vertical tail dynamic pressure*Vertical tail area)
Vertical tail lift curve slope for given moment
Go Vertical tail Lift curve slope = Moment produced by vertical tail/(Vertical tail moment arm*(Sideslip angle+Sidewash angle)*Vertical tail dynamic pressure*Vertical tail area)
Vertical tail area for given moment
Go Vertical tail area = Moment produced by vertical tail/(Vertical tail moment arm*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)*Vertical tail dynamic pressure)
Moment produced by vertical tail for given lift curve slope
Go Moment produced by vertical tail = Vertical tail moment arm*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)*Vertical tail dynamic pressure*Vertical tail area
Vertical tail lift curve slope for given yawing moment coefficient and Vertical Tail Efficiency
Go Vertical tail Lift curve slope = Yawing moment coefficient/(Vertical Tail Volume Ratio*Vertical tail efficiency*(Sideslip angle+Sidewash angle))
Vertical tail volume ratio for given yawing moment coefficient
Go Vertical Tail Volume Ratio = Yawing moment coefficient/(Vertical tail efficiency*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle))
Vertical tail efficiency for given yawing moment coefficient
Go Vertical tail efficiency = Yawing moment coefficient/(Vertical Tail Volume Ratio*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle))
Vertical tail dynamic pressure for given vertical tail side force
Go Vertical tail dynamic pressure = -Vertical Tail Side Force/(Vertical tail Lift curve slope*Vertical tail angle of attack*Vertical tail area)
Vertical tail angle of attack for given vertical tail side force
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
Go Vertical tail Lift curve slope = -Vertical Tail Side Force/(Vertical tail angle of attack*Vertical tail dynamic pressure*Vertical tail area)
Vertical tail area for given vertical tail side force
Go Vertical tail area = Vertical Tail Side Force/(Vertical tail Lift curve slope*Vertical tail angle of attack*Vertical tail dynamic pressure)
Vertical tail Side force
Go Vertical Tail Side Force = -Vertical tail Lift curve slope*Vertical tail angle of attack*Vertical tail area*Vertical tail dynamic pressure
Moment produced by vertical tail for given moment coefficient
Go Moment produced by vertical tail = Yawing moment coefficient*Wing dynamic pressure*Wingspan*Reference Area
Vertical tail volume ratio
Go Vertical Tail Volume Ratio = Vertical tail moment arm*Vertical tail area/(Reference Area*Wingspan)
Vertical tail moment arm for given vertical tail volume ratio
Go Vertical tail moment arm = Vertical Tail Volume Ratio*Reference Area*Wingspan/Vertical tail area
Vertical tail area for given vertical tail volume ratio
Go Vertical tail area = Vertical Tail Volume Ratio*Reference Area*Wingspan/Vertical tail moment arm
Moment produced by vertical tail for given side force
Go Moment produced by vertical tail = Vertical tail moment arm*Vertical Tail Side Force
Vertical tail moment arm for given side force
Go Vertical tail moment arm = Moment produced by vertical tail/Vertical Tail Side Force
Vertical tail side force for given moment
Go Vertical Tail Side Force = Moment produced by vertical tail/Vertical tail moment arm
Vertical tail efficiency
Go Vertical tail efficiency = Vertical tail dynamic pressure/Wing dynamic pressure
Vertical tail angle of attack
Go Vertical tail angle of attack = Sidewash angle+Sideslip angle

Moment produced by vertical tail for given side force Formula

Moment produced by vertical tail = Vertical tail moment arm*Vertical Tail Side Force
Nv = ๐’v*Yv

What causes Dutch roll in aircraft?

Dutch roll is a natural aerodynamic phenomenon in swept-wing aircraft. It is caused by design having slightly weaker directional stability than lateral stability.

How to Calculate Moment produced by vertical tail for given side force?

Moment produced by vertical tail for given side force calculator uses Moment produced by vertical tail = Vertical tail moment arm*Vertical Tail Side Force to calculate the Moment produced by vertical tail, The Moment produced by vertical tail for given side force is the product of the vertical tail moment arm and side force acting on it. Moment produced by vertical tail is denoted by Nv symbol.

How to calculate Moment produced by vertical tail for given side force using this online calculator? To use this online calculator for Moment produced by vertical tail for given side force, enter Vertical tail moment arm (๐’v) & Vertical Tail Side Force (Yv) and hit the calculate button. Here is how the Moment produced by vertical tail for given side force calculation can be explained with given input values -> 7.2 = 1.2*(-6.12).

FAQ

What is Moment produced by vertical tail for given side force?
The Moment produced by vertical tail for given side force is the product of the vertical tail moment arm and side force acting on it and is represented as Nv = ๐’v*Yv or Moment produced by vertical tail = Vertical tail moment arm*Vertical Tail Side Force. 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 Side Force is the side force acting on the vertical tail of an aircraft.
How to calculate Moment produced by vertical tail for given side force?
The Moment produced by vertical tail for given side force is the product of the vertical tail moment arm and side force acting on it is calculated using Moment produced by vertical tail = Vertical tail moment arm*Vertical Tail Side Force. To calculate Moment produced by vertical tail for given side force, you need Vertical tail moment arm (๐’v) & Vertical Tail Side Force (Yv). With our tool, you need to enter the respective value for Vertical tail moment arm & Vertical Tail Side Force 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 Moment produced by vertical tail?
In this formula, Moment produced by vertical tail uses Vertical tail moment arm & Vertical Tail Side Force. We can use 2 other way(s) to calculate the same, which is/are as follows -
  • Moment produced by vertical tail = Vertical tail moment arm*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)*Vertical tail dynamic pressure*Vertical tail area
  • Moment produced by vertical tail = Yawing moment coefficient*Wing dynamic pressure*Wingspan*Reference Area
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