Tail Pitching moment for given lift coefficient Calculator

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Static Stability and Control

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Longitudinal Stability

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Wing-Tail Contribution

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

✖Pitching Moment due to Tail is the pitching moment of the tail about the aircraft's center of gravity.ⓘ Tail Pitching moment for given lift coefficient [M_t]

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Formula

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Tail Pitching moment for given lift coefficient

Formula

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

Example

`"-218.252241N*m"=-("0.8m"*"0.3"*"1.225kg/m³"*("28.72m/s")^2*"1.8m²")/2`

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Tail Pitching moment for given lift coefficient Solution

STEP 0: Pre-Calculation Summary

Formula Used

Pitching Moment due to Tail = -(Horizontal tail moment arm*Tail Lift Coefficient*Freestream Density*Tail Velocity^2*Horizontal tail area)/2
M_t = -(𝒍_t*CT_lift*ρ_∞*V_t^2*S_t)/2
This formula uses 6 Variables

Variables Used

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.
Tail Lift Coefficient - Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity.
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

Horizontal tail moment arm: 0.8 Meter --> 0.8 Meter No Conversion Required
Tail Lift Coefficient: 0.3 --> 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

M_t = -(𝒍_t*CT_lift*ρ_∞*V_t^2*S_t)/2 --> -(0.8*0.3*1.225*28.72^2*1.8)/2

Evaluating ... ...

M_t = -218.25224064

STEP 3: Convert Result to Output's Unit

-218.25224064 Newton Meter --> No Conversion Required

FINAL ANSWER

-218.25224064 ≈ -218.252241 Newton Meter <-- Pitching Moment due to Tail

(Calculation completed in 00.004 seconds)

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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!

< 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 Pitching moment for given lift coefficient Formula

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

Why does aft CG save fuel?

A CG near the aft reduces drag by reducing the necessary downforce that has to be supplied (usually) by the tailplane.

How to Calculate Tail Pitching moment for given lift coefficient?

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

How to calculate Tail Pitching moment for given lift coefficient using this online calculator? To use this online calculator for Tail Pitching moment for given lift coefficient, enter Horizontal tail moment arm (𝒍_t), Tail Lift Coefficient (CT_lift), Freestream Density (ρ_∞), Tail Velocity (V_t) & Horizontal tail area (S_t) and hit the calculate button. Here is how the Tail Pitching moment for given lift coefficient calculation can be explained with given input values -> -218.252241 = -(0.8*0.3*1.225*28.72^2*1.8)/2.

FAQ

What is Tail Pitching moment for given lift coefficient?

The Tail Pitching moment for given lift coefficient is a function of the tail moment arm, tail lift coefficient, the altitude of aircraft, the velocity of the tail, and area of the tail and is represented as M_t = -(𝒍_t*CT_lift*ρ_∞*V_t^2*S_t)/2 or Pitching Moment due to Tail = -(Horizontal tail moment arm*Tail Lift Coefficient*Freestream Density*Tail Velocity^2*Horizontal tail area)/2. The horizontal tail moment arm is the distance between the lift center of the horizontal tail and the center of gravity of the aircraft, Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity, 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 Pitching moment for given lift coefficient?

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

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

Pitching Moment due to Tail = -Horizontal tail moment arm*Lift due to tail
Pitching Moment due to Tail = (Tail Pitching Moment Coefficient*Freestream Density*Flight Velocity^2*Reference Area*Mean aerodynamic chord)/2

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