Tail lift coefficient for given pitching moment Calculator

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Wing-Tail Contribution

Fuselage Contribution

Tail Contribution

✖Pitching Moment due to Tail is the pitching moment of the tail about the aircraft's center of gravity.ⓘ Pitching Moment due to Tail [M_t]			+10% -10%
✖The horizontal tail moment arm is the distance between the lift center of the horizontal tail and the center of gravity of the aircraft.ⓘ Horizontal tail moment arm [𝒍_t]			+10% -10%
✖Freestream Density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.ⓘ Freestream Density [ρ_∞]			+10% -10%
✖Tail Velocity is the velocity of the horizontal tail of an aircraft.ⓘ Tail Velocity [V_t]			+10% -10%
✖The Horizontal tail area is the area of the horizontal tail of an aircraft.ⓘ Horizontal tail area [S_t]			+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 pitching moment [CT_lift]

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Formula

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Tail lift coefficient for given pitching moment

Formula

`"CT"_{"lift"} = -2*"M"_{"t"}/("𝒍"_{"t"}*"ρ"_{"∞"}*"V"_{"t"}^2*"S"_{"t"})`

Example

`"0.300244"=-2*"-218.43N*m"/("0.8m"*"1.225kg/m³"*("28.72m/s")^2*"1.8m²")`

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Tail lift coefficient for given pitching moment Solution

STEP 0: Pre-Calculation Summary

Formula Used

Tail Lift Coefficient = -2*Pitching Moment due to Tail/(Horizontal tail moment arm*Freestream Density*Tail Velocity^2*Horizontal tail area)
CT_lift = -2*M_t/(𝒍_t*ρ_∞*V_t^2*S_t)
This formula uses 6 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.
Pitching Moment due to Tail - (Measured in Newton Meter) - Pitching Moment due to Tail is the pitching moment of the tail about the aircraft's center of gravity.
Horizontal tail moment arm - (Measured in Meter) - The horizontal tail moment arm is the distance between the lift center of the horizontal tail and the center of gravity of the aircraft.
Freestream Density - (Measured in Kilogram per Cubic Meter) - Freestream Density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude.
Tail Velocity - (Measured in Meter per Second) - Tail Velocity is the velocity of the horizontal tail of an aircraft.
Horizontal tail area - (Measured in Square Meter) - The Horizontal tail area is the area of the horizontal tail of an aircraft.

STEP 1: Convert Input(s) to Base Unit

Pitching Moment due to Tail: -218.43 Newton Meter --> -218.43 Newton Meter No Conversion Required
Horizontal tail moment arm: 0.8 Meter --> 0.8 Meter No Conversion Required
Freestream Density: 1.225 Kilogram per Cubic Meter --> 1.225 Kilogram per Cubic Meter No Conversion Required
Tail Velocity: 28.72 Meter per Second --> 28.72 Meter per Second No Conversion Required
Horizontal tail area: 1.8 Square Meter --> 1.8 Square Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

CT_lift = -2*M_t/(𝒍_t*ρ_∞*V_t^2*S_t) --> -2*(-218.43)/(0.8*1.225*28.72^2*1.8)

Evaluating ... ...

CT_lift = 0.300244340254394

STEP 3: Convert Result to Output's Unit

0.300244340254394 --> No Conversion Required

FINAL ANSWER

0.300244340254394 ≈ 0.300244 <-- Tail Lift Coefficient

(Calculation completed in 00.004 seconds)

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Home » Physics » Aircraft Mechanics » Static Stability and Control » Longitudinal Stability » Wing-Tail Contribution » Tail lift coefficient for given pitching moment

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 Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

Maiarutselvan V has verified this Calculator and 300+ more calculators!

< 15 Wing-Tail Contribution Calculators

Tail lift coefficient for given pitching moment coefficient

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

Tail lift coefficient for given pitching moment

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

Tail Lift Coefficient of wing-tail combination

Go Tail Lift Coefficient = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Efficiency*Horizontal tail area)

Tail Efficiency for given lift coefficients

Go Tail Efficiency = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Lift Coefficient*Horizontal tail area)

Tail area for given tail efficiency

Go Horizontal tail area = Reference Area*(Lift Coefficient-Wing Lift Coefficient)/(Tail Lift Coefficient*Tail Efficiency)

Total Lift Coefficient of wing-tail combination

Go Lift Coefficient = Wing Lift Coefficient+(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient/Reference Area)

Wing Lift Coefficient of wing-tail combination

Go Wing Lift Coefficient = Lift Coefficient-(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient/Reference Area)

Angle of incidence of wing

Go Wing incidence angle = Wing angle of attack-Horizontal tail angle of attack-Downwash angle+Tail incidence angle

Angle of incidence of tail

Go Tail incidence angle = Horizontal tail angle of attack-Wing angle of attack+Wing incidence angle+Downwash angle

Angle of Attack at Tail

Go Horizontal tail angle of attack = Wing angle of attack-Wing incidence angle-Downwash angle+Tail incidence angle

Angle of attack of wing

Go Wing angle of attack = Horizontal tail angle of attack+Wing incidence angle+Downwash angle-Tail incidence angle

Downwash angle

Go Downwash angle = Wing angle of attack-Wing incidence angle-Horizontal tail angle of attack+Tail incidence angle

Total Lift of wing-tail combination

Go Lift Force = Lift due to wing+Lift due to tail

Lift due to wing only

Go Lift due to wing = Lift Force-Lift due to tail

Lift due to tail only

Go Lift due to tail = Lift Force-Lift due to wing

Tail lift coefficient for given pitching moment Formula

Tail Lift Coefficient = -2*Pitching Moment due to Tail/(Horizontal tail moment arm*Freestream Density*Tail Velocity^2*Horizontal tail area)
CT_lift = -2*M_t/(𝒍_t*ρ_∞*V_t^2*S_t)

What does aft CG mean?

The aft CG limit is the most rearward position at which the CG can be located for the most critical maneuver or operation. As the CG moves aft, a less stable condition occurs, which decreases the aircraft's ability to right itself after maneuvering or turbulence.

How to Calculate Tail lift coefficient for given pitching moment?

Tail lift coefficient for given pitching moment calculator uses Tail Lift Coefficient = -2*Pitching Moment due to Tail/(Horizontal tail moment arm*Freestream Density*Tail Velocity^2*Horizontal tail area) to calculate the Tail Lift Coefficient, The Tail lift coefficient for given pitching moment is a function of moment arm, altitude, tail velocity, tail area, and pitching moment of the tail of aircraft. Tail Lift Coefficient is denoted by CT_lift symbol.

How to calculate Tail lift coefficient for given pitching moment using this online calculator? To use this online calculator for Tail lift coefficient for given pitching moment, enter Pitching Moment due to Tail (M_t), Horizontal tail moment arm (𝒍_t), Freestream Density (ρ_∞), Tail Velocity (V_t) & Horizontal tail area (S_t) and hit the calculate button. Here is how the Tail lift coefficient for given pitching moment calculation can be explained with given input values -> 0.300244 = -2*(-218.43)/(0.8*1.225*28.72^2*1.8).

FAQ

What is Tail lift coefficient for given pitching moment?

The Tail lift coefficient for given pitching moment is a function of moment arm, altitude, tail velocity, tail area, and pitching moment of the tail of aircraft and is represented as CT_lift = -2*M_t/(𝒍_t*ρ_∞*V_t^2*S_t) or Tail Lift Coefficient = -2*Pitching Moment due to Tail/(Horizontal tail moment arm*Freestream Density*Tail Velocity^2*Horizontal tail area). Pitching Moment due to Tail is the pitching moment of the tail about the aircraft's center of gravity, The horizontal tail moment arm is the distance between the lift center of the horizontal tail and the center of gravity of the aircraft, Freestream Density is the mass per unit volume of air far upstream of an aerodynamic body at a given altitude, Tail Velocity is the velocity of the horizontal tail of an aircraft & The Horizontal tail area is the area of the horizontal tail of an aircraft.

How to calculate Tail lift coefficient for given pitching moment?

The Tail lift coefficient for given pitching moment is a function of moment arm, altitude, tail velocity, tail area, and pitching moment of the tail of aircraft is calculated using Tail Lift Coefficient = -2*Pitching Moment due to Tail/(Horizontal tail moment arm*Freestream Density*Tail Velocity^2*Horizontal tail area). To calculate Tail lift coefficient for given pitching moment, you need Pitching Moment due to Tail (M_t), Horizontal tail moment arm (𝒍_t), Freestream Density (ρ_∞), Tail Velocity (V_t) & Horizontal tail area (S_t). With our tool, you need to enter the respective value for Pitching Moment due to Tail, Horizontal tail moment arm, Freestream Density, Tail Velocity & Horizontal tail 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 Tail Lift Coefficient?

In this formula, Tail Lift Coefficient uses Pitching Moment due to Tail, Horizontal tail moment arm, Freestream Density, Tail Velocity & Horizontal tail area. We can use 2 other way(s) to calculate the same, which is/are as follows -

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

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