Moment produced by vertical tail for given moment coefficient Solution

STEP 0: Pre-Calculation Summary
Formula Used
Moment produced by vertical tail = Yawing moment coefficient*Wing dynamic pressure*Wingspan*Reference Area
Nv = Cn*Qw*b*S
This formula uses 5 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.
Yawing moment coefficient - Yawing moment coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis.
Wing dynamic pressure - (Measured in Pascal) - Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft.
Wingspan - (Measured in Meter) - The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.
Reference Area - (Measured in Square Meter) - The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.
STEP 1: Convert Input(s) to Base Unit
Yawing moment coefficient: 1.4 --> No Conversion Required
Wing dynamic pressure: 0.66 Pascal --> 0.66 Pascal No Conversion Required
Wingspan: 50 Meter --> 50 Meter No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
Nv = Cn*Qw*b*S --> 1.4*0.66*50*5.08
Evaluating ... ...
Nv = 234.696
STEP 3: Convert Result to Output's Unit
234.696 Newton Meter --> No Conversion Required
FINAL ANSWER
234.696 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
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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 moment coefficient Formula

Moment produced by vertical tail = Yawing moment coefficient*Wing dynamic pressure*Wingspan*Reference Area
Nv = Cn*Qw*b*S

What is tail down force?

The elevator (or stabilator) of an aircraft balances out the torque by creating another downward force, called tail-down force, by generating torque in the opposite direction. Essentially, the tail is an 'upside down' wing that generates lift downward.

How to Calculate Moment produced by vertical tail for given moment coefficient?

Moment produced by vertical tail for given moment coefficient calculator uses Moment produced by vertical tail = Yawing moment coefficient*Wing dynamic pressure*Wingspan*Reference Area to calculate the Moment produced by vertical tail, The Moment produced by vertical tail for given moment coefficient depends on the dynamic pressure at the wing, wingspan, and wing area. Moment produced by vertical tail is denoted by Nv symbol.

How to calculate Moment produced by vertical tail for given moment coefficient using this online calculator? To use this online calculator for Moment produced by vertical tail for given moment coefficient, enter Yawing moment coefficient (Cn), Wing dynamic pressure (Qw), Wingspan (b) & Reference Area (S) and hit the calculate button. Here is how the Moment produced by vertical tail for given moment coefficient calculation can be explained with given input values -> 234.696 = 1.4*0.66*50*5.08.

FAQ

What is Moment produced by vertical tail for given moment coefficient?
The Moment produced by vertical tail for given moment coefficient depends on the dynamic pressure at the wing, wingspan, and wing area and is represented as Nv = Cn*Qw*b*S or Moment produced by vertical tail = Yawing moment coefficient*Wing dynamic pressure*Wingspan*Reference Area. Yawing moment coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis, Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft, The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip & The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.
How to calculate Moment produced by vertical tail for given moment coefficient?
The Moment produced by vertical tail for given moment coefficient depends on the dynamic pressure at the wing, wingspan, and wing area is calculated using Moment produced by vertical tail = Yawing moment coefficient*Wing dynamic pressure*Wingspan*Reference Area. To calculate Moment produced by vertical tail for given moment coefficient, you need Yawing moment coefficient (Cn), Wing dynamic pressure (Qw), Wingspan (b) & Reference Area (S). With our tool, you need to enter the respective value for Yawing moment coefficient, Wing dynamic pressure, Wingspan & Reference 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 Moment produced by vertical tail?
In this formula, Moment produced by vertical tail uses Yawing moment coefficient, Wing dynamic pressure, Wingspan & Reference Area. 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 Side Force
  • 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
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