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Vertical tail lift curve slope for given yawing moment coefficient Calculator

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✖Yawing moment coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis.ⓘ Yawing moment coefficient [Cn]
+10%
-10%
✖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.ⓘ Reference Area [S]
+10%
-10%
✖The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.ⓘ Wingspan [b]
+10%
-10%
✖Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft.ⓘ Wing dynamic pressure [Qw]
+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 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%
✖Vertical tail dynamic pressure is the dynamic pressure associated with the vertical tail of an aircraft.ⓘ Vertical tail dynamic pressure [Qv]
+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 [β]
+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 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 for given yawing moment coefficient [Cv]
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Formula
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Vertical tail lift curve slope for given yawing moment coefficient

Formula
`"C"_{"v"} = "C"_{"n"}*"S"*"b"*"Q"_{"w"}/("𝒍"_{"v"}*"S"_{"v"}*"Q"_{"v"}*("β"+"σ"))`

Example
`"30.39316rad⁻¹"="1.4"*"5.08m²"*"50m"*"0.66Pa"/("1.2m"*"5m²"*"11Pa"*("0.05rad"+"0.067rad"))`

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Vertical tail lift curve slope for given yawing moment coefficient Solution

STEP 0: Pre-Calculation Summary
Formula Used
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))
Cv = Cn*S*b*Qw/(𝒍v*Sv*Qv*(β+σ))
This formula uses 10 Variables
Variables Used
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.
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.
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.
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.
Wing dynamic pressure - (Measured in Pascal) - Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft.
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 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.
Vertical tail dynamic pressure - (Measured in Pascal) - Vertical tail dynamic pressure is the dynamic pressure associated with the vertical tail 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
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Wingspan: 50 Meter --> 50 Meter No Conversion Required
Wing dynamic pressure: 0.66 Pascal --> 0.66 Pascal No Conversion Required
Vertical tail moment arm: 1.2 Meter --> 1.2 Meter No Conversion Required
Vertical tail area: 5 Square Meter --> 5 Square Meter No Conversion Required
Vertical tail dynamic pressure: 11 Pascal --> 11 Pascal 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
Cv = Cn*S*b*Qw/(𝒍v*Sv*Qv*(β+σ)) --> 1.4*5.08*50*0.66/(1.2*5*11*(0.05+0.067))
Evaluating ... ...
Cv = 30.3931623931624
STEP 3: Convert Result to Output's Unit
30.3931623931624 1 per Radian --> No Conversion Required
FINAL ANSWER
30.3931623931624 ≈ 30.39316 1 per Radian <-- Vertical tail Lift curve slope
(Calculation completed in 00.004 seconds)
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Home » Physics » Aircraft Mechanics » Static Stability and Control » Directional Stability » Vertical Tail Contribution » Vertical tail lift curve slope for given yawing moment coefficient

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
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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 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 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 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
Vertical tail moment arm for given side force
Go Vertical tail moment arm = -Moment produced by vertical tail/Vertical Tail Side Force
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 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 lift curve slope for given yawing moment coefficient Formula

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))
Cv = Cn*S*b*Qw/(𝒍v*Sv*Qv*(β+σ))

Which flap gives the best lift coefficient?

The double-slotted flap increases the maximum lift coefficient in the same way the single-slotted flap does – by delaying flow separation over the flap element. The key difference is that the double-slotted flap adds a level of boundary-layer control not possible with the single-slotted one.

How to Calculate Vertical tail lift curve slope for given yawing moment coefficient?

Vertical tail lift curve slope for given yawing moment coefficient calculator uses 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)) to calculate the Vertical tail Lift curve slope, The Vertical tail lift curve slope for given yawing moment coefficient is a function of the vertical tail's moment arm, dynamic pressure (at vertical tail), area, sideslip angle, sidewash angle, wing's reference area, wingspan, and dynamic pressure at wing. Vertical tail Lift curve slope is denoted by Cv symbol.

How to calculate Vertical tail lift curve slope for given yawing moment coefficient using this online calculator? To use this online calculator for Vertical tail lift curve slope for given yawing moment coefficient, enter Yawing moment coefficient (Cn), Reference Area (S), Wingspan (b), Wing dynamic pressure (Qw), Vertical tail moment arm (𝒍v), Vertical tail area (Sv), Vertical tail dynamic pressure (Qv), Sideslip angle (β) & Sidewash angle (σ) and hit the calculate button. Here is how the Vertical tail lift curve slope for given yawing moment coefficient calculation can be explained with given input values -> 30.39316 = 1.4*5.08*50*0.66/(1.2*5*11*(0.05+0.067)).

FAQ

What is Vertical tail lift curve slope for given yawing moment coefficient?
The Vertical tail lift curve slope for given yawing moment coefficient is a function of the vertical tail's moment arm, dynamic pressure (at vertical tail), area, sideslip angle, sidewash angle, wing's reference area, wingspan, and dynamic pressure at wing and is represented as Cv = Cn*S*b*Qw/(𝒍v*Sv*Qv*(β+σ)) or 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)). Yawing moment coefficient is the coefficient associated with the moment that tends to rotate an airplane about its vertical (or yaw) axis, 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, The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip, Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft, 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 area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline, Vertical tail dynamic pressure is the dynamic pressure associated with the vertical tail 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 lift curve slope for given yawing moment coefficient?
The Vertical tail lift curve slope for given yawing moment coefficient is a function of the vertical tail's moment arm, dynamic pressure (at vertical tail), area, sideslip angle, sidewash angle, wing's reference area, wingspan, and dynamic pressure at wing is calculated using 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)). To calculate Vertical tail lift curve slope for given yawing moment coefficient, you need Yawing moment coefficient (Cn), Reference Area (S), Wingspan (b), Wing dynamic pressure (Qw), Vertical tail moment arm (𝒍v), Vertical tail area (Sv), Vertical tail dynamic pressure (Qv), Sideslip angle (β) & Sidewash angle (σ). With our tool, you need to enter the respective value for Yawing moment coefficient, Reference Area, Wingspan, Wing dynamic pressure, Vertical tail moment arm, Vertical tail area, Vertical tail dynamic pressure, 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 Lift curve slope?
In this formula, Vertical tail Lift curve slope uses Yawing moment coefficient, Reference Area, Wingspan, Wing dynamic pressure, Vertical tail moment arm, Vertical tail area, Vertical tail dynamic pressure, Sideslip angle & Sidewash angle. We can use 3 other way(s) to calculate the same, which is/are as follows -
  • Vertical tail Lift curve slope = -Vertical Tail Side Force/(Vertical tail angle of attack*Vertical tail dynamic pressure*Vertical tail area)
  • 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 Lift curve slope = Yawing moment coefficient/(Vertical Tail Volume Ratio*Vertical tail efficiency*(Sideslip angle+Sidewash angle))
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