Tail lift coefficient for given tail volume ratio Calculator

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Static Stability and Control

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Longitudinal Stability

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Wing-Tail Contribution

✖Tail Pitching Moment Coefficient is the coefficient of pitching moment associated with the horizontal tail of an aircraft.ⓘ Tail Pitching Moment Coefficient [Cm_t]			+10% -10%
✖Horizontal Tail Volume Ratio relates the area of the horizontal tail, the distance between tail and aircraft's c.g., the wing area, and the mean aerodynamic wing chord.ⓘ Horizontal Tail Volume Ratio [V_H]			+10% -10%
✖Tail Efficiency is defined as the ratio of dynamic pressure associated with the tail to dynamic pressure associated with an aircraft's wing.ⓘ Tail Efficiency [η]			+10% -10%

✖Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity.ⓘ Tail lift coefficient for given tail volume ratio [CT_lift]

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Tail lift coefficient for given tail volume ratio

Formula

`"CT"_{"lift"} = -"Cm"_{"t"}/("V"_{"H"}*"η")`

Example

`"0.29853"=-"-0.39"/("1.42"*"0.92")`

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Tail lift coefficient for given tail volume ratio Solution

STEP 0: Pre-Calculation Summary

Formula Used

Tail Lift Coefficient = -Tail Pitching Moment Coefficient/(Horizontal Tail Volume Ratio*Tail Efficiency)
CT_lift = -Cm_t/(V_H*η)
This formula uses 4 Variables

Variables Used

Tail Lift Coefficient - Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity.
Tail Pitching Moment Coefficient - Tail Pitching Moment Coefficient is the coefficient of pitching moment associated with the horizontal tail of an aircraft.
Horizontal Tail Volume Ratio - Horizontal Tail Volume Ratio relates the area of the horizontal tail, the distance between tail and aircraft's c.g., the wing area, and the mean aerodynamic wing chord.
Tail Efficiency - Tail Efficiency is defined as the ratio of dynamic pressure associated with the tail to dynamic pressure associated with an aircraft's wing.

STEP 1: Convert Input(s) to Base Unit

Tail Pitching Moment Coefficient: -0.39 --> No Conversion Required
Horizontal Tail Volume Ratio: 1.42 --> No Conversion Required
Tail Efficiency: 0.92 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

CT_lift = -Cm_t/(V_H*η) --> -(-0.39)/(1.42*0.92)

Evaluating ... ...

CT_lift = 0.298530312308634

STEP 3: Convert Result to Output's Unit

0.298530312308634 --> No Conversion Required

FINAL ANSWER

0.298530312308634 ≈ 0.29853 <-- Tail Lift Coefficient

(Calculation completed in 00.004 seconds)

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Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

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Verified by Sanjay Krishna

Amrita School of Engineering (ASE), Vallikavu

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< 19 Tail Contribution Calculators

Tail Pitching moment coefficient for given tail efficiency

Go Tail Pitching Moment Coefficient = -(Tail Efficiency*Horizontal tail area*Horizontal tail moment arm*Tail Lift Coefficient)/(Reference Area*Mean aerodynamic chord)

Tail Efficiency for given pitching moment coefficient

Go Tail Efficiency = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Horizontal tail moment arm*Horizontal tail area*Tail Lift Coefficient)

Tail moment arm for given tail moment coefficient

Go Horizontal tail moment arm = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient)

Tail area for given tail moment coefficient

Go Horizontal tail area = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Tail Efficiency*Horizontal tail moment arm*Tail Lift Coefficient)

Mean aerodynamic chord for given tail pitching moment coefficient

Go Mean aerodynamic chord = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Tail Pitching Moment Coefficient)

Tail Pitching moment coefficient

Go Tail Pitching Moment Coefficient = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Mean aerodynamic chord)

Tail Pitching moment for given moment coefficient

Go Pitching Moment due to Tail = (Tail Pitching Moment Coefficient*Freestream Density*Flight Velocity^2*Reference Area*Mean aerodynamic chord)/2

Tail Pitching moment for given lift coefficient

Go Pitching Moment due to Tail = -(Horizontal tail moment arm*Tail Lift Coefficient*Freestream Density*Tail Velocity^2*Horizontal tail area)/2

Wing Mean aerodynamic chord for given horizontal tail volume ratio

Go Mean aerodynamic chord = Horizontal tail moment arm*Horizontal tail area/(Reference Area*Horizontal Tail Volume Ratio)

Wing Reference area for given horizontal tail volume ratio

Go Reference Area = Horizontal tail moment arm*Horizontal tail area/(Horizontal Tail Volume Ratio*Mean aerodynamic chord)

Horizontal tail volume ratio

Go Horizontal Tail Volume Ratio = Horizontal tail moment arm*Horizontal tail area/(Reference Area*Mean aerodynamic chord)

Tail moment arm for given horizontal tail volume ratio

Go Horizontal tail moment arm = Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail area

Horizontal tail area for given tail volume ratio

Go Horizontal tail area = Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail moment arm

Horizontal tail volume ratio for given pitching moment coefficient

Go Horizontal Tail Volume Ratio = -Tail Pitching Moment Coefficient/(Tail Efficiency*Tail Lift Coefficient)

Tail lift coefficient for given tail volume ratio

Go Tail Lift Coefficient = -Tail Pitching Moment Coefficient/(Horizontal Tail Volume Ratio*Tail Efficiency)

Tail Efficiency for given tail volume ratio

Go Tail Efficiency = -Tail Pitching Moment Coefficient/(Horizontal Tail Volume Ratio*Tail Lift Coefficient)

Tail Pitching moment coefficient for given tail volume ratio

Go Tail Pitching Moment Coefficient = -Horizontal Tail Volume Ratio*Tail Efficiency*Tail Lift Coefficient

Tail lift for given tail pitching moment

Go Lift due to tail = -Pitching Moment due to Tail/Horizontal tail moment arm

Pitching moment due to tail

Go Pitching Moment due to Tail = -Horizontal tail moment arm*Lift due to tail

Tail lift coefficient for given tail volume ratio Formula

Tail Lift Coefficient = -Tail Pitching Moment Coefficient/(Horizontal Tail Volume Ratio*Tail Efficiency)
CT_lift = -Cm_t/(V_H*η)

What is the difference between maneuverability and controllability?

Controllability of an aircraft is the capability of an aircraft to respond to the pilots' control inputs, and maneuverability is the aircraft's quality that can be easily controlled in the given space region.

How to Calculate Tail lift coefficient for given tail volume ratio?

Tail lift coefficient for given tail volume ratio calculator uses Tail Lift Coefficient = -Tail Pitching Moment Coefficient/(Horizontal Tail Volume Ratio*Tail Efficiency) to calculate the Tail Lift Coefficient, The Tail lift coefficient for given tail volume ratio depends on the tail pitching moment coefficient and tail efficiency. Tail Lift Coefficient is denoted by CT_lift symbol.

How to calculate Tail lift coefficient for given tail volume ratio using this online calculator? To use this online calculator for Tail lift coefficient for given tail volume ratio, enter Tail Pitching Moment Coefficient (Cm_t), Horizontal Tail Volume Ratio (V_H) & Tail Efficiency (η) and hit the calculate button. Here is how the Tail lift coefficient for given tail volume ratio calculation can be explained with given input values -> 0.301811 = -(-0.39)/(1.42*0.92).

FAQ

What is Tail lift coefficient for given tail volume ratio?

The Tail lift coefficient for given tail volume ratio depends on the tail pitching moment coefficient and tail efficiency and is represented as CT_lift = -Cm_t/(V_H*η) or Tail Lift Coefficient = -Tail Pitching Moment Coefficient/(Horizontal Tail Volume Ratio*Tail Efficiency). Tail Pitching Moment Coefficient is the coefficient of pitching moment associated with the horizontal tail of an aircraft, Horizontal Tail Volume Ratio relates the area of the horizontal tail, the distance between tail and aircraft's c.g., the wing area, and the mean aerodynamic wing chord & Tail Efficiency is defined as the ratio of dynamic pressure associated with the tail to dynamic pressure associated with an aircraft's wing.

How to calculate Tail lift coefficient for given tail volume ratio?

The Tail lift coefficient for given tail volume ratio depends on the tail pitching moment coefficient and tail efficiency is calculated using Tail Lift Coefficient = -Tail Pitching Moment Coefficient/(Horizontal Tail Volume Ratio*Tail Efficiency). To calculate Tail lift coefficient for given tail volume ratio, you need Tail Pitching Moment Coefficient (Cm_t), Horizontal Tail Volume Ratio (V_H) & Tail Efficiency (η). With our tool, you need to enter the respective value for Tail Pitching Moment Coefficient, Horizontal Tail Volume Ratio & Tail Efficiency and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

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