Wing Reference area for given horizontal tail volume ratio 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%
✖The Horizontal tail area is the area of the horizontal tail of an aircraft.ⓘ Horizontal tail area [S_t]			+10% -10%
✖Horizontal Tail Volume Ratio relates the area of the horizontal tail, the distance between tail and aircraft's c.g., the wing area, and the mean aerodynamic wing chord.ⓘ Horizontal Tail Volume Ratio [V_H]			+10% -10%
✖The Mean aerodynamic chord is a two-dimensional representation of the whole wing.ⓘ Mean aerodynamic chord [c_ma]			+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.ⓘ Wing Reference area for given horizontal tail volume ratio [S]

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Formula

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Wing Reference area for given horizontal tail volume ratio

Formula

`"S" = "𝒍"_{"t"}*"S"_{"t"}/("V"_{"H"}*"c"_{"ma"})`

Example

`"5.070423m²"="0.8m"*"1.8m²"/("1.42"*"0.2m")`

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Wing Reference area for given horizontal tail volume ratio Solution

STEP 0: Pre-Calculation Summary

Formula Used

Reference Area = Horizontal tail moment arm*Horizontal tail area/(Horizontal Tail Volume Ratio*Mean aerodynamic chord)
S = 𝒍_t*S_t/(V_H*c_ma)
This formula uses 5 Variables

Variables Used

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.
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.
Horizontal tail area - (Measured in Square Meter) - The Horizontal tail area is the area of the horizontal tail of an aircraft.
Horizontal Tail Volume Ratio - Horizontal Tail Volume Ratio relates the area of the horizontal tail, the distance between tail and aircraft's c.g., the wing area, and the mean aerodynamic wing chord.
Mean aerodynamic chord - (Measured in Meter) - The Mean aerodynamic chord is a two-dimensional representation of the whole wing.

STEP 1: Convert Input(s) to Base Unit

Horizontal tail moment arm: 0.8 Meter --> 0.8 Meter No Conversion Required
Horizontal tail area: 1.8 Square Meter --> 1.8 Square Meter No Conversion Required
Horizontal Tail Volume Ratio: 1.42 --> No Conversion Required
Mean aerodynamic chord: 0.2 Meter --> 0.2 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

S = 𝒍_t*S_t/(V_H*c_ma) --> 0.8*1.8/(1.42*0.2)

Evaluating ... ...

S = 5.07042253521127

STEP 3: Convert Result to Output's Unit

5.07042253521127 Square Meter --> No Conversion Required

FINAL ANSWER

5.07042253521127 ≈ 5.070423 Square Meter <-- Reference Area

(Calculation completed in 00.004 seconds)

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Home » Physics » Aircraft Mechanics » Static Stability and Control » Longitudinal Stability » Tail Contribution » Wing Reference area for given horizontal tail volume ratio

Credits

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 Shikha Maurya

Indian Institute of Technology (IIT), Bombay

Shikha Maurya has verified this Calculator and 200+ 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

Wing Reference area for given horizontal tail volume ratio Formula

Reference Area = Horizontal tail moment arm*Horizontal tail area/(Horizontal Tail Volume Ratio*Mean aerodynamic chord)
S = 𝒍_t*S_t/(V_H*c_ma)

What is taper ratio for wings?

Taper ratio is one of the parameters on planform geometry, which means the ratio of the wing's root and tip chord lengths. Hence, its effects on the wing's aerodynamic parameters are also essential and should be considered during a wing design process.

How to Calculate Wing Reference area for given horizontal tail volume ratio?

Wing Reference area for given horizontal tail volume ratio calculator uses Reference Area = Horizontal tail moment arm*Horizontal tail area/(Horizontal Tail Volume Ratio*Mean aerodynamic chord) to calculate the Reference Area, The Wing Reference area for given horizontal tail volume ratio depends on the tail moment arm, tail area, tail volume ratio, and mean aerodynamic chord of the wing. Reference Area is denoted by S symbol.

How to calculate Wing Reference area for given horizontal tail volume ratio using this online calculator? To use this online calculator for Wing Reference area for given horizontal tail volume ratio, enter Horizontal tail moment arm (𝒍_t), Horizontal tail area (S_t), Horizontal Tail Volume Ratio (V_H) & Mean aerodynamic chord (c_ma) and hit the calculate button. Here is how the Wing Reference area for given horizontal tail volume ratio calculation can be explained with given input values -> 5.106383 = 0.8*1.8/(1.42*0.2).

FAQ

What is Wing Reference area for given horizontal tail volume ratio?

The Wing Reference area for given horizontal tail volume ratio depends on the tail moment arm, tail area, tail volume ratio, and mean aerodynamic chord of the wing and is represented as S = 𝒍_t*S_t/(V_H*c_ma) or Reference Area = Horizontal tail moment arm*Horizontal tail area/(Horizontal Tail Volume Ratio*Mean aerodynamic chord). The horizontal tail moment arm is the distance between the lift center of the horizontal tail and the center of gravity of the aircraft, The Horizontal tail area is the area of the horizontal tail of an aircraft, Horizontal Tail Volume Ratio relates the area of the horizontal tail, the distance between tail and aircraft's c.g., the wing area, and the mean aerodynamic wing chord & The Mean aerodynamic chord is a two-dimensional representation of the whole wing.

How to calculate Wing Reference area for given horizontal tail volume ratio?

The Wing Reference area for given horizontal tail volume ratio depends on the tail moment arm, tail area, tail volume ratio, and mean aerodynamic chord of the wing is calculated using Reference Area = Horizontal tail moment arm*Horizontal tail area/(Horizontal Tail Volume Ratio*Mean aerodynamic chord). To calculate Wing Reference area for given horizontal tail volume ratio, you need Horizontal tail moment arm (𝒍_t), Horizontal tail area (S_t), Horizontal Tail Volume Ratio (V_H) & Mean aerodynamic chord (c_ma). With our tool, you need to enter the respective value for Horizontal tail moment arm, Horizontal tail area, Horizontal Tail Volume Ratio & Mean aerodynamic chord 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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