Wing Lift Coefficient of wing-tail combination Calculator

✖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 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 [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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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 surface area of the horizontal stabilizer on an aircraft, which provides pitch stability and control.
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

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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

Wing Lift Coefficient of wing-tail combination Formula

LaTeX Go

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, Wing Lift Coefficient of wing-tail combination is a measure of the overall lift characteristics of an aircraft, taking into account the contributions of the wing and tail components, and is used to evaluate the stability and performance of the aircraft during flight. 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 -> 1.010205 = 1.108-(0.92*1.8*0.3/5.08).

FAQ

What is Wing Lift Coefficient of wing-tail combination?

Wing Lift Coefficient of wing-tail combination is a measure of the overall lift characteristics of an aircraft, taking into account the contributions of the wing and tail components, and is used to evaluate the stability and performance of the aircraft during flight 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 surface area of the horizontal stabilizer on an aircraft, which provides pitch stability and control, 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?

Wing Lift Coefficient of wing-tail combination is a measure of the overall lift characteristics of an aircraft, taking into account the contributions of the wing and tail components, and is used to evaluate the stability and performance of the aircraft during flight 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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