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Sideslip angle for given moment produced by vertical tail Calculator

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✖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.ⓘ Moment produced by vertical tail [Nv]
+10%
-10%
✖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 moment arm [𝒍v]
+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 [Cv]
+10%
-10%
✖Vertical tail dynamic pressure is the dynamic pressure associated with the vertical tail of an aircraft.ⓘ Vertical tail dynamic pressure [Qv]
+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 [Sv]
+10%
-10%
✖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.ⓘ Sidewash angle [σ]
+10%
-10%
✖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.ⓘ Sideslip angle for given moment produced by vertical tail [β]
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Formula
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Sideslip angle for given moment produced by vertical tail

Formula
`"β" = ("N"_{"v"}/("𝒍"_{"v"}*"C"_{"v"}*"Q"_{"v"}*"S"_{"v"}))-"σ"`

Example
`"-0.02371rad"=("2N*m"/("1.2m"*"0.7rad⁻¹"*"11Pa"*"5m²"))-"0.067rad"`

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Sideslip angle for given moment produced by vertical tail Solution

STEP 0: Pre-Calculation Summary
Formula Used
Sideslip angle = (Moment produced by vertical tail/(Vertical tail moment arm*Vertical tail Lift curve slope*Vertical tail dynamic pressure*Vertical tail area))-Sidewash angle
β = (Nv/(𝒍v*Cv*Qv*Sv))-σ
This formula uses 7 Variables
Variables Used
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.
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 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 dynamic pressure - (Measured in Pascal) - Vertical tail dynamic pressure is the dynamic pressure associated with the vertical tail 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.
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
Moment produced by vertical tail: 2 Newton Meter --> 2 Newton Meter No Conversion Required
Vertical tail moment arm: 1.2 Meter --> 1.2 Meter No Conversion Required
Vertical tail Lift curve slope: 0.7 1 per Radian --> 0.7 1 per Radian No Conversion Required
Vertical tail dynamic pressure: 11 Pascal --> 11 Pascal No Conversion Required
Vertical tail area: 5 Square Meter --> 5 Square Meter No Conversion Required
Sidewash angle: 0.067 Radian --> 0.067 Radian No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
β = (Nv/(𝒍v*Cv*Qv*Sv))-σ --> (2/(1.2*0.7*11*5))-0.067
Evaluating ... ...
β = -0.0237099567099567
STEP 3: Convert Result to Output's Unit
-0.0237099567099567 Radian --> No Conversion Required
FINAL ANSWER
-0.0237099567099567 ≈ -0.02371 Radian <-- Sideslip angle
(Calculation completed in 00.004 seconds)
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Home » Physics » Aircraft Mechanics » Static Stability and Control » Directional Stability » Aerodynamic Parameters » Sideslip angle for given moment produced by vertical tail

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!

10+ Aerodynamic Parameters Calculators

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

Sideslip angle for given moment produced by vertical tail Formula

Sideslip angle = (Moment produced by vertical tail/(Vertical tail moment arm*Vertical tail Lift curve slope*Vertical tail dynamic pressure*Vertical tail area))-Sidewash angle
β = (Nv/(𝒍v*Cv*Qv*Sv))-σ

What is a skid in aviation?

Skid is an aerodynamic condition, during a turn, where the tail of an aeroplane moves away from the centre of the turn or tends to follow a path which is outside that followed by the nose.

How to Calculate Sideslip angle for given moment produced by vertical tail?

Sideslip angle for given moment produced by vertical tail calculator uses Sideslip angle = (Moment produced by vertical tail/(Vertical tail moment arm*Vertical tail Lift curve slope*Vertical tail dynamic pressure*Vertical tail area))-Sidewash angle to calculate the Sideslip angle, The Sideslip angle for given moment produced by vertical tail depends on the vertical tail's moment arm, lift curve slope, dynamic pressure, area, and sidewash angle. Sideslip angle is denoted by β symbol.

How to calculate Sideslip angle for given moment produced by vertical tail using this online calculator? To use this online calculator for Sideslip angle for given moment produced by vertical tail, enter Moment produced by vertical tail (Nv), Vertical tail moment arm (𝒍v), Vertical tail Lift curve slope (Cv), Vertical tail dynamic pressure (Qv), Vertical tail area (Sv) & Sidewash angle (σ) and hit the calculate button. Here is how the Sideslip angle for given moment produced by vertical tail calculation can be explained with given input values -> -0.02371 = (2/(1.2*0.7*11*5))-0.067.

FAQ

What is Sideslip angle for given moment produced by vertical tail?
The Sideslip angle for given moment produced by vertical tail depends on the vertical tail's moment arm, lift curve slope, dynamic pressure, area, and sidewash angle and is represented as β = (Nv/(𝒍v*Cv*Qv*Sv))-σ or Sideslip angle = (Moment produced by vertical tail/(Vertical tail moment arm*Vertical tail Lift curve slope*Vertical tail dynamic pressure*Vertical tail area))-Sidewash angle. 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, The vertical tail moment arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft, The Vertical tail Lift curve slope is the slope associated with the lift curve of a vertical tailplane of an aircraft, Vertical tail dynamic pressure is the dynamic pressure associated with the vertical tail 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 & 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 Sideslip angle for given moment produced by vertical tail?
The Sideslip angle for given moment produced by vertical tail depends on the vertical tail's moment arm, lift curve slope, dynamic pressure, area, and sidewash angle is calculated using Sideslip angle = (Moment produced by vertical tail/(Vertical tail moment arm*Vertical tail Lift curve slope*Vertical tail dynamic pressure*Vertical tail area))-Sidewash angle. To calculate Sideslip angle for given moment produced by vertical tail, you need Moment produced by vertical tail (Nv), Vertical tail moment arm (𝒍v), Vertical tail Lift curve slope (Cv), Vertical tail dynamic pressure (Qv), Vertical tail area (Sv) & Sidewash angle (σ). With our tool, you need to enter the respective value for Moment produced by vertical tail, Vertical tail moment arm, Vertical tail Lift curve slope, Vertical tail dynamic pressure, Vertical tail area & 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 Sideslip angle?
In this formula, Sideslip angle uses Moment produced by vertical tail, Vertical tail moment arm, Vertical tail Lift curve slope, Vertical tail dynamic pressure, Vertical tail area & Sidewash angle. We can use 2 other way(s) to calculate the same, which is/are as follows -
  • Sideslip angle = Vertical tail angle of attack-Sidewash angle
  • Sideslip angle = (Yawing moment coefficient/(Vertical Tail Volume Ratio*Vertical tail efficiency*Vertical tail Lift curve slope))-Sidewash angle
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