Wing Lift Coefficient of wing-tail combination Calculator

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Static Stability and Control

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Wing-Tail Contribution

Fuselage Contribution

Tail Contribution

✖The Lift Coefficient is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area.ⓘ Lift Coefficient [C_L]			+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%
✖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 [CT_lift]			+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%

✖Wing Lift Coefficient is the lift coefficient associated with the wing (only) of an aircraft. It is a dimensionless quantity.ⓘ Wing Lift Coefficient of wing-tail combination [CW_lift]

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Formula

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Wing Lift Coefficient of wing-tail combination

Formula

`"CW"_{"lift"} = "C"_{"L"}-("η"*"S"_{"t"}*"CT"_{"lift"}/"S")`

Example

`"1.010205"="1.108"-("0.92"*"1.8m²"*"0.3"/"5.08m²")`

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Wing Lift Coefficient of wing-tail combination Solution

STEP 0: Pre-Calculation Summary

Formula Used

Wing Lift Coefficient = Lift Coefficient-(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient/Reference Area)
CW_lift = C_L-(η*S_t*CT_lift/S)
This formula uses 6 Variables

Variables Used

Wing Lift Coefficient - Wing Lift Coefficient is the lift coefficient associated with the wing (only) of an aircraft. It is a dimensionless quantity.
Lift Coefficient - The Lift Coefficient is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area.
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.
Horizontal tail area - (Measured in Square Meter) - The Horizontal tail area is the area of the horizontal tail of an aircraft.
Tail Lift Coefficient - Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity.
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.

STEP 1: Convert Input(s) to Base Unit

Lift Coefficient: 1.108 --> No Conversion Required
Tail Efficiency: 0.92 --> No Conversion Required
Horizontal tail area: 1.8 Square Meter --> 1.8 Square Meter No Conversion Required
Tail Lift Coefficient: 0.3 --> No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

CW_lift = C_L-(η*S_t*CT_lift/S) --> 1.108-(0.92*1.8*0.3/5.08)

Evaluating ... ...

CW_lift = 1.01020472440945

STEP 3: Convert Result to Output's Unit

1.01020472440945 --> No Conversion Required

FINAL ANSWER

1.01020472440945 ≈ 1.010205 <-- Wing 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

Vinay Mishra has created this Calculator and 300+ more calculators!

Verified by Maiarutselvan V

PSG College of Technology (PSGCT), Coimbatore

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< 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

Wing Lift Coefficient of wing-tail combination Formula

Wing Lift Coefficient = Lift Coefficient-(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient/Reference Area)
CW_lift = C_L-(η*S_t*CT_lift/S)

What is the purpose of the horizontal tail wing?

The function of the tailplane is to provide stability and control. In particular, the tailplane helps adjust for changes in the position of the centre of pressure or centre of gravity caused by changes in speed and attitude, fuel consumption, or dropping cargo or payload.

How to Calculate Wing Lift Coefficient of wing-tail combination?

Wing Lift Coefficient of wing-tail combination calculator uses Wing Lift Coefficient = Lift Coefficient-(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient/Reference Area) to calculate the Wing Lift Coefficient, The Wing Lift Coefficient of wing-tail combination is dependent on the total lift coefficient, tail efficiency, horizontal tail area, and lift coefficient of the horizontal tail of an aircraft. Wing Lift Coefficient is denoted by CW_lift symbol.

How to calculate Wing Lift Coefficient of wing-tail combination using this online calculator? To use this online calculator for Wing Lift Coefficient of wing-tail combination, enter Lift Coefficient (C_L), Tail Efficiency (η), Horizontal tail area (S_t), Tail Lift Coefficient (CT_lift) & Reference Area (S) and hit the calculate button. Here is how the Wing Lift Coefficient of wing-tail combination calculation can be explained with given input values -> 1.002205 = 1.108-(0.92*1.8*0.3/5.08).

FAQ

What is Wing Lift Coefficient of wing-tail combination?

The Wing Lift Coefficient of wing-tail combination is dependent on the total lift coefficient, tail efficiency, horizontal tail area, and lift coefficient of the horizontal tail of an aircraft and is represented as CW_lift = C_L-(η*S_t*CT_lift/S) or Wing Lift Coefficient = Lift Coefficient-(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient/Reference Area). The Lift Coefficient is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area, Tail Efficiency is defined as the ratio of dynamic pressure associated with the tail to dynamic pressure associated with an aircraft's wing, The Horizontal tail area is the area of the horizontal tail of an aircraft, Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity & 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.

How to calculate Wing Lift Coefficient of wing-tail combination?

The Wing Lift Coefficient of wing-tail combination is dependent on the total lift coefficient, tail efficiency, horizontal tail area, and lift coefficient of the horizontal tail of an aircraft is calculated using Wing Lift Coefficient = Lift Coefficient-(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient/Reference Area). To calculate Wing Lift Coefficient of wing-tail combination, you need Lift Coefficient (C_L), Tail Efficiency (η), Horizontal tail area (S_t), Tail Lift Coefficient (CT_lift) & Reference Area (S). With our tool, you need to enter the respective value for Lift Coefficient, Tail Efficiency, Horizontal tail area, Tail Lift Coefficient & Reference Area 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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