Vertical tail efficiency for given yawing moment coefficient Solution

STEP 0: Pre-Calculation Summary
Formula Used
Vertical tail efficiency = Yawing moment coefficient/(Vertical Tail Volume Ratio*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle))
ηv = Cn/(Vv*Cv*(β+σ))
This formula uses 6 Variables
Variables Used
Vertical tail efficiency - Vertical tail efficiency is the tail efficiency associated with the vertical tail of an aircraft.
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.
Vertical Tail Volume Ratio - Vertical Tail Volume Ratio relates the area of the vertical tail, the distance between the centroid of vertical tail area and aircraft's c.g., the wing area, and the wingspan.
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.
Sideslip angle - (Measured in Radian) - The sideslip angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind.
Sidewash angle - (Measured in Radian) - Sidewash angle is caused by the flow field distortion due to the wings and fuselage. It is analogous to the downwash angle for the horizontal tailplane.
STEP 1: Convert Input(s) to Base Unit
Yawing moment coefficient: 1.4 --> No Conversion Required
Vertical Tail Volume Ratio: 1.5 --> No Conversion Required
Vertical tail Lift curve slope: 0.7 1 per Radian --> 0.7 1 per Radian No Conversion Required
Sideslip angle: 0.05 Radian --> 0.05 Radian No Conversion Required
Sidewash angle: 0.067 Radian --> 0.067 Radian No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
ηv = Cn/(Vv*Cv*(β+σ)) --> 1.4/(1.5*0.7*(0.05+0.067))
Evaluating ... ...
ηv = 11.3960113960114
STEP 3: Convert Result to Output's Unit
11.3960113960114 --> No Conversion Required
FINAL ANSWER
11.3960113960114 11.39601 <-- Vertical tail efficiency
(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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National Institute Of Technology (NIT), Hamirpur
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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

Vertical tail efficiency for given yawing moment coefficient Formula

Vertical tail efficiency = Yawing moment coefficient/(Vertical Tail Volume Ratio*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle))
ηv = Cn/(Vv*Cv*(β+σ))

What does the tail efficiency factor depend on?

The tail efficiency factor depends on the tail location with respect to the airplane wake and slipstream of the engine and power effects.

How to Calculate Vertical tail efficiency for given yawing moment coefficient?

Vertical tail efficiency for given yawing moment coefficient calculator uses Vertical tail efficiency = Yawing moment coefficient/(Vertical Tail Volume Ratio*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)) to calculate the Vertical tail efficiency, Vertical tail efficiency for given yawing moment coefficient is a function of vertical tail volume ratio, vertical tail lift curve slope, sideslip angle and sidewash angle. Vertical tail efficiency is denoted by ηv symbol.

How to calculate Vertical tail efficiency for given yawing moment coefficient using this online calculator? To use this online calculator for Vertical tail efficiency for given yawing moment coefficient, enter Yawing moment coefficient (Cn), Vertical Tail Volume Ratio (Vv), Vertical tail Lift curve slope (Cv), Sideslip angle (β) & Sidewash angle (σ) and hit the calculate button. Here is how the Vertical tail efficiency for given yawing moment coefficient calculation can be explained with given input values -> 11.39601 = 1.4/(1.5*0.7*(0.05+0.067)).

FAQ

What is Vertical tail efficiency for given yawing moment coefficient?
Vertical tail efficiency for given yawing moment coefficient is a function of vertical tail volume ratio, vertical tail lift curve slope, sideslip angle and sidewash angle and is represented as ηv = Cn/(Vv*Cv*(β+σ)) or Vertical tail efficiency = Yawing moment coefficient/(Vertical Tail Volume Ratio*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)). Yawing moment coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis, Vertical Tail Volume Ratio relates the area of the vertical tail, the distance between the centroid of vertical tail area and aircraft's c.g., the wing area, and the wingspan, The Vertical tail Lift curve slope is the slope associated with the lift curve of a vertical tailplane of an aircraft, The sideslip angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind & Sidewash angle is caused by the flow field distortion due to the wings and fuselage. It is analogous to the downwash angle for the horizontal tailplane.
How to calculate Vertical tail efficiency for given yawing moment coefficient?
Vertical tail efficiency for given yawing moment coefficient is a function of vertical tail volume ratio, vertical tail lift curve slope, sideslip angle and sidewash angle is calculated using Vertical tail efficiency = Yawing moment coefficient/(Vertical Tail Volume Ratio*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)). To calculate Vertical tail efficiency for given yawing moment coefficient, you need Yawing moment coefficient (Cn), Vertical Tail Volume Ratio (Vv), Vertical tail Lift curve slope (Cv), Sideslip angle (β) & Sidewash angle (σ). With our tool, you need to enter the respective value for Yawing moment coefficient, Vertical Tail Volume Ratio, Vertical tail Lift curve slope, Sideslip angle & Sidewash angle 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 efficiency?
In this formula, Vertical tail efficiency uses Yawing moment coefficient, Vertical Tail Volume Ratio, Vertical tail Lift curve slope, Sideslip angle & Sidewash angle. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Vertical tail efficiency = Vertical tail dynamic pressure/Wing dynamic pressure
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