Vertical tail moment arm for given side force Solution

STEP 0: Pre-Calculation Summary
Formula Used
Vertical tail moment arm = Moment produced by vertical tail/Vertical Tail Side Force
๐’v = Nv/Yv
This formula uses 3 Variables
Variables Used
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.
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 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
Moment produced by vertical tail: 2 Newton Meter --> 2 Newton 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
๐’v = Nv/Yv --> 2/(-6.12)
Evaluating ... ...
๐’v = -0.326797385620915
STEP 3: Convert Result to Output's Unit
-0.326797385620915 Meter --> No Conversion Required
FINAL ANSWER
-0.326797385620915 โ‰ˆ -0.326797 Meter <-- Vertical tail moment arm
(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
Shikha Maurya has verified this Calculator and 200+ more calculators!

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

Vertical tail moment arm for given side force Formula

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

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At the rear of the fuselage of most aircraft one finds a horizontal stabilizer and an elevator. The stabilizer is a fixed-wing section whose job is to provide stability for the aircraft, to keep it flying straight. The horizontal stabilizer prevents up-and-down, or pitching, the motion of the aircraft nose.

How to Calculate Vertical tail moment arm for given side force?

Vertical tail moment arm for given side force calculator uses Vertical tail moment arm = Moment produced by vertical tail/Vertical Tail Side Force to calculate the Vertical tail moment arm, The Vertical tail moment arm for given side force is the distance between center of gravity of the wing and the aerodynamic center of the stab. Vertical tail moment arm is denoted by ๐’v symbol.

How to calculate Vertical tail moment arm for given side force using this online calculator? To use this online calculator for Vertical tail moment arm for given side force, enter Moment produced by vertical tail (Nv) & Vertical Tail Side Force (Yv) and hit the calculate button. Here is how the Vertical tail moment arm for given side force calculation can be explained with given input values -> -0.326797 = 2/(-6.12).

FAQ

What is Vertical tail moment arm for given side force?
The Vertical tail moment arm for given side force is the distance between center of gravity of the wing and the aerodynamic center of the stab and is represented as ๐’v = Nv/Yv or Vertical tail moment arm = Moment produced by vertical tail/Vertical Tail Side Force. 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 Side Force is the side force acting on the vertical tail of an aircraft.
How to calculate Vertical tail moment arm for given side force?
The Vertical tail moment arm for given side force is the distance between center of gravity of the wing and the aerodynamic center of the stab is calculated using Vertical tail moment arm = Moment produced by vertical tail/Vertical Tail Side Force. To calculate Vertical tail moment arm for given side force, you need Moment produced by vertical tail (Nv) & Vertical Tail Side Force (Yv). With our tool, you need to enter the respective value for Moment produced by vertical tail & 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 Vertical tail moment arm?
In this formula, Vertical tail moment arm uses Moment produced by vertical tail & Vertical Tail Side Force. We can use 3 other way(s) to calculate the same, which is/are as follows -
  • 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 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 moment arm = Vertical Tail Volume Ratio*Reference Area*Wingspan/Vertical tail area
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