Total Lift Coefficient of Wing-Tail Combination Calculator

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

✖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.ⓘ Total Lift Coefficient of Wing-Tail Combination [C_L]

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Total Lift Coefficient of Wing-Tail Combination Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

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

Wing Lift Coefficient: 1.01 --> 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

C_L = CW_lift+(η*S_t*CT_lift/S) --> 1.01+(0.92*1.8*0.3/5.08)

Evaluating ... ...

C_L = 1.10779527559055

STEP 3: Convert Result to Output's Unit

1.10779527559055 --> No Conversion Required

FINAL ANSWER

1.10779527559055 ≈ 1.107795 <-- 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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Indian Institute of Technology (IIT), Bombay

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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

Total Lift Coefficient of Wing-Tail Combination Formula

LaTeX Go

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

What is empennage of an aircraft?

The empennage is the name given to the entire tail section of the aircraft, including both the horizontal and vertical stabilizers, the rudder and the elevator.

How to Calculate Total Lift Coefficient of Wing-Tail Combination?

Total Lift Coefficient of Wing-Tail Combination calculator uses Lift Coefficient = Wing Lift Coefficient+(Tail Efficiency*Horizontal Tail Area*Tail Lift Coefficient/Reference Area) to calculate the Lift Coefficient, Total Lift Coefficient of Wing-Tail Combination is a measure of the overall lifting ability of an aircraft, taking into account the individual lift coefficients of the wing and tail, as well as the efficiency of the tail and its area relative to the reference area. Lift Coefficient is denoted by C_L symbol.

How to calculate Total Lift Coefficient of Wing-Tail Combination using this online calculator? To use this online calculator for Total Lift Coefficient of Wing-Tail Combination, enter Wing Lift Coefficient (CW_lift), 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 Total Lift Coefficient of Wing-Tail Combination calculation can be explained with given input values -> 1.107795 = 1.01+(0.92*1.8*0.3/5.08).

FAQ

What is Total Lift Coefficient of Wing-Tail Combination?

Total Lift Coefficient of Wing-Tail Combination is a measure of the overall lifting ability of an aircraft, taking into account the individual lift coefficients of the wing and tail, as well as the efficiency of the tail and its area relative to the reference area and is represented as C_L = CW_lift+(η*S_t*CT_lift/S) or Lift Coefficient = Wing Lift Coefficient+(Tail Efficiency*Horizontal Tail Area*Tail Lift Coefficient/Reference Area). Wing Lift Coefficient is the lift coefficient associated with the wing (only) of an aircraft. It is a dimensionless quantity, 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 Total Lift Coefficient of Wing-Tail Combination?

Total Lift Coefficient of Wing-Tail Combination is a measure of the overall lifting ability of an aircraft, taking into account the individual lift coefficients of the wing and tail, as well as the efficiency of the tail and its area relative to the reference area is calculated using Lift Coefficient = Wing Lift Coefficient+(Tail Efficiency*Horizontal Tail Area*Tail Lift Coefficient/Reference Area). To calculate Total Lift Coefficient of Wing-Tail Combination, you need Wing Lift Coefficient (CW_lift), 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 Wing 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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