Tail Lift Coefficient for given Pitching Moment Calculator

✖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%
✖Velocity Tail refers to the airspeed or velocity of the horizontal stabilizer (tail) of an aircraft relative to the surrounding air (relative wind).ⓘ Velocity Tail [V_tail]			+10% -10%
✖The Horizontal Tail Area is the surface area of the horizontal stabilizer on an aircraft, which provides pitch stability and control.ⓘ 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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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*Velocity Tail^2*Horizontal Tail Area)
CT_lift = -2*M_t/(𝒍_t*ρ_∞*V_tail^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.
Velocity Tail - (Measured in Meter per Second) - Velocity Tail refers to the airspeed or velocity of the horizontal stabilizer (tail) of an aircraft relative to the surrounding air (relative wind).
Horizontal Tail Area - (Measured in Square Meter) - The Horizontal Tail Area is the surface area of the horizontal stabilizer on an aircraft, which provides pitch stability and control.

STEP 1: Convert Input(s) to Base Unit

Pitching Moment due to Tail: -218.6644 Newton Meter --> -218.6644 Newton Meter No Conversion Required
Horizontal Tail Moment Arm: 0.801511 Meter --> 0.801511 Meter No Conversion Required
Freestream Density: 1.225 Kilogram per Cubic Meter --> 1.225 Kilogram per Cubic Meter No Conversion Required
Velocity Tail: 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_tail^2*S_t) --> -2*(-218.6644)/(0.801511*1.225*28.72^2*1.8)

Evaluating ... ...

CT_lift = 0.299999911426611

STEP 3: Convert Result to Output's Unit

0.299999911426611 --> No Conversion Required

FINAL ANSWER

0.299999911426611 ≈ 0.3 <-- 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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PSG College of Technology (PSGCT), Coimbatore

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< Wing Tail Contribution Calculators

Angle of incidence of wing

LaTeX Go Wing Incidence Angle = Wing Angle of Attack-Horizontal Tail Angle of Attack-Downwash Angle+Tail Incidence Angle

Angle of Attack at Tail

LaTeX Go Horizontal Tail Angle of Attack = Wing Angle of Attack-Wing Incidence Angle-Downwash Angle+Tail Incidence Angle

Angle of Attack of Wing

LaTeX Go Wing Angle of Attack = Horizontal Tail Angle of Attack+Wing Incidence Angle+Downwash Angle-Tail Incidence Angle

Downwash angle

LaTeX Go Downwash Angle = Wing Angle of Attack-Wing Incidence Angle-Horizontal Tail Angle of Attack+Tail Incidence Angle

Tail Lift Coefficient for given Pitching Moment Formula

LaTeX Go

Tail Lift Coefficient = -2*Pitching Moment due to Tail/(Horizontal Tail Moment Arm*Freestream Density*Velocity Tail^2*Horizontal Tail Area)
CT_lift = -2*M_t/(𝒍_t*ρ_∞*V_tail^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*Velocity Tail^2*Horizontal Tail Area) to calculate the Tail Lift Coefficient, Tail Lift Coefficient for given Pitching Moment is a dimensionless quantity that characterizes the rotating motion of the horizontal tail, influenced by the pitching moment, horizontal tail moment arm, freestream density, tail velocity, and horizontal tail area, enabling the calculation of the tail's lift force in aerodynamic systems. 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_∞), Velocity Tail (V_tail) & 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 -> 0.3 = -2*(-218.6644)/(0.801511*1.225*28.72^2*1.8).

FAQ

What is Tail Lift Coefficient for given Pitching Moment?

Tail Lift Coefficient for given Pitching Moment is a dimensionless quantity that characterizes the rotating motion of the horizontal tail, influenced by the pitching moment, horizontal tail moment arm, freestream density, tail velocity, and horizontal tail area, enabling the calculation of the tail's lift force in aerodynamic systems and is represented as CT_lift = -2*M_t/(𝒍_t*ρ_∞*V_tail^2*S_t) or Tail Lift Coefficient = -2*Pitching Moment due to Tail/(Horizontal Tail Moment Arm*Freestream Density*Velocity Tail^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, Velocity Tail refers to the airspeed or velocity of the horizontal stabilizer (tail) of an aircraft relative to the surrounding air (relative wind) & The Horizontal Tail Area is the surface area of the horizontal stabilizer on an aircraft, which provides pitch stability and control.

How to calculate Tail Lift Coefficient for given Pitching Moment?

Tail Lift Coefficient for given Pitching Moment is a dimensionless quantity that characterizes the rotating motion of the horizontal tail, influenced by the pitching moment, horizontal tail moment arm, freestream density, tail velocity, and horizontal tail area, enabling the calculation of the tail's lift force in aerodynamic systems is calculated using Tail Lift Coefficient = -2*Pitching Moment due to Tail/(Horizontal Tail Moment Arm*Freestream Density*Velocity Tail^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_∞), Velocity Tail (V_tail) & 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, Velocity Tail & 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, Velocity Tail & 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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