Wing Mean Aerodynamic Chord for given Horizontal Tail Volume Ratio Calculator

✖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 surface area of the horizontal stabilizer on an aircraft, which provides pitch stability and control.ⓘ 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 \cdot \frac{S t}{S \cdot V H}

Example

0.2 m = 0.801511 m \cdot \frac{1.8 m²}{5.08 m² \cdot 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 surface area of the horizontal stabilizer on an aircraft, which provides pitch stability and control.
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: 0.801511 Meter --> 0.801511 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) --> 0.801511*1.8/(5.08*1.42)

Evaluating ... ...

c_ma = 0.199999972274592

STEP 3: Convert Result to Output's Unit

0.199999972274592 Meter --> No Conversion Required

FINAL ANSWER

0.199999972274592 ≈ 0.2 Meter <-- Mean Aerodynamic Chord

(Calculation completed in 00.004 seconds)

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Home » Physics » Aircraft Mechanics » Static Stability and Control » Longitudinal Stability » Aerospace » Tail Contribution » Wing Mean Aerodynamic Chord for given Horizontal Tail Volume Ratio

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

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< Tail Contribution Calculators

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*Velocity Tail^2*Horizontal Tail Area)/2

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)

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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, Wing Mean Aerodynamic Chord for given Horizontal Tail Volume Ratio is a measure of the average distance from the root to the tip of a wing, calculated in relation to the horizontal tail's volume ratio, area, and moment arm, providing a vital parameter for aircraft design and stability analysis. 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 -> 0.2 = 0.801511*1.8/(5.08*1.42).

FAQ

What is Wing Mean Aerodynamic Chord for given Horizontal Tail Volume Ratio?

Wing Mean Aerodynamic Chord for given Horizontal Tail Volume Ratio is a measure of the average distance from the root to the tip of a wing, calculated in relation to the horizontal tail's volume ratio, area, and moment arm, providing a vital parameter for aircraft design and stability analysis 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 surface area of the horizontal stabilizer on an aircraft, which provides pitch stability and control, 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?

Wing Mean Aerodynamic Chord for given Horizontal Tail Volume Ratio is a measure of the average distance from the root to the tip of a wing, calculated in relation to the horizontal tail's volume ratio, area, and moment arm, providing a vital parameter for aircraft design and stability analysis 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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