Wing Mean aerodynamic chord 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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Fuselage Contribution

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%
✖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%
✖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.ⓘ Wing Mean aerodynamic chord for given horizontal tail volume ratio [c_ma]

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Formula

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Wing Mean aerodynamic chord for given horizontal tail volume ratio

Formula

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

Example

`"0.199623m"="0.8m"*"1.8m²"/("5.08m²"*"1.42")`

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Wing Mean aerodynamic chord for given horizontal tail volume ratio Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

Mean aerodynamic chord - (Measured in Meter) - The Mean aerodynamic chord is a two-dimensional representation of the whole wing.
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.
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 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.

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
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Horizontal Tail Volume Ratio: 1.42 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

c_ma = 𝒍_t*S_t/(S*V_H) --> 0.8*1.8/(5.08*1.42)

Evaluating ... ...

c_ma = 0.199622934457137

STEP 3: Convert Result to Output's Unit

0.199622934457137 Meter --> No Conversion Required

FINAL ANSWER

0.199622934457137 ≈ 0.199623 Meter <-- Mean aerodynamic chord

(Calculation completed in 00.004 seconds)

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Home » Physics » Aircraft Mechanics » Static Stability and Control » Longitudinal Stability » Tail Contribution » Wing Mean aerodynamic chord for given horizontal tail volume ratio

Credits

Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

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Verified by Shikha Maurya

Indian Institute of Technology (IIT), Bombay

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< 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 Mean aerodynamic chord for given horizontal tail volume ratio Formula

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

Does stall speed change with weight?

Stall speed increases as weight increases since wings need to fly at a higher angle of attack to generate enough lift for a given airspeed.

How to Calculate Wing Mean aerodynamic chord for given horizontal tail volume ratio?

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

How to calculate Wing Mean aerodynamic chord for given horizontal tail volume ratio using this online calculator? To use this online calculator for Wing Mean aerodynamic chord for given horizontal tail volume ratio, enter Horizontal tail moment arm (𝒍_t), Horizontal tail area (S_t), Reference Area (S) & Horizontal Tail Volume Ratio (V_H) and hit the calculate button. Here is how the Wing Mean aerodynamic chord for given horizontal tail volume ratio calculation can be explained with given input values -> 0.201039 = 0.8*1.8/(5.08*1.42).

FAQ

What is Wing Mean aerodynamic chord for given horizontal tail volume ratio?

The Wing Mean aerodynamic chord for given horizontal tail volume ratio depends on the tail moment arm, tail area, wing area, and tail volume ratio and is represented as c_ma = 𝒍_t*S_t/(S*V_H) or Mean aerodynamic chord = Horizontal tail moment arm*Horizontal tail area/(Reference Area*Horizontal Tail Volume Ratio). 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, 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 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.

How to calculate Wing Mean aerodynamic chord for given horizontal tail volume ratio?

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

In this formula, Mean aerodynamic chord uses Horizontal tail moment arm, Horizontal tail area, Reference Area & Horizontal Tail Volume Ratio. We can use 1 other way(s) to calculate the same, which is/are as follows -

Mean aerodynamic chord = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Tail Pitching Moment Coefficient)

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