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%
✖The Mean Aerodynamic Chord is a two-dimensional representation of the whole wing.ⓘ Mean Aerodynamic Chord [c_ma]			+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]

⎘ Copy

👎

Formula

LaTeX

Reset

👍

Download Tail Contribution Formulas PDF PDF Image

Horizontal tail volume ratio Solution

STEP 0: Pre-Calculation Summary

Formula Used

Horizontal Tail Volume Ratio = Horizontal Tail Moment Arm*Horizontal Tail Area/(Reference Area*Mean Aerodynamic Chord)
V_H = 𝒍_t*S_t/(S*c_ma)
This formula uses 5 Variables

Variables Used

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.
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.
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: 0.801511 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
Mean Aerodynamic Chord: 0.2 Meter --> 0.2 Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

V_H = 𝒍_t*S_t/(S*c_ma) --> 0.801511*1.8/(5.08*0.2)

Evaluating ... ...

V_H = 1.41999980314961

STEP 3: Convert Result to Output's Unit

1.41999980314961 --> No Conversion Required

FINAL ANSWER

1.41999980314961 ≈ 1.42 <-- Horizontal Tail Volume Ratio

(Calculation completed in 00.020 seconds)

You are here -

Home » Physics » Aircraft Mechanics » Static Stability and Control » Longitudinal Stability » Aerospace » Tail Contribution » 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!

< Tail Contribution Calculators

Tail Pitching Moment for given Moment Coefficient

LaTeX 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

LaTeX 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

LaTeX Go Lift due to Tail = -(Pitching Moment due to Tail/Horizontal Tail Moment Arm)

Pitching Moment due to Tail

LaTeX Go Pitching Moment due to Tail = -Horizontal Tail Moment Arm*Lift due to Tail

Horizontal tail volume ratio Formula

LaTeX Go

Horizontal Tail Volume Ratio = Horizontal Tail Moment Arm*Horizontal Tail Area/(Reference Area*Mean Aerodynamic Chord)
V_H = 𝒍_t*S_t/(S*c_ma)

Why does deflecting the elevators down create an upward lift?

If you deflect the elevator, an aileron, or the flaps downward, each surface always creates a lift force in an upward direction. The reason for this behavior is that the air has to follow a longer path over the top, which creates a lower pressure that results in a lift.

How to Calculate Horizontal tail volume ratio?

Horizontal tail volume ratio calculator uses Horizontal Tail Volume Ratio = Horizontal Tail Moment Arm*Horizontal Tail Area/(Reference Area*Mean Aerodynamic Chord) to calculate the Horizontal Tail Volume Ratio, Horizontal Tail Volume Ratio is a dimensionless parameter that characterizes the size and shape of an aircraft's horizontal tail surface, it is a crucial factor in determining the stability and control of an aircraft during flight, this ratio is calculated by dividing the product of the horizontal tail moment arm and area by the reference area and mean aerodynamic chord. Horizontal Tail Volume Ratio is denoted by V_H symbol.

How to calculate Horizontal tail volume ratio using this online calculator? To use this online calculator for Horizontal tail volume ratio, enter Horizontal Tail Moment Arm (𝒍_t), Horizontal Tail Area (S_t), Reference Area (S) & Mean Aerodynamic Chord (c_ma) and hit the calculate button. Here is how the Horizontal tail volume ratio calculation can be explained with given input values -> 1.42 = 0.801511*1.8/(5.08*0.2).

FAQ

What is Horizontal tail volume ratio?

Horizontal Tail Volume Ratio is a dimensionless parameter that characterizes the size and shape of an aircraft's horizontal tail surface, it is a crucial factor in determining the stability and control of an aircraft during flight, this ratio is calculated by dividing the product of the horizontal tail moment arm and area by the reference area and mean aerodynamic chord and is represented as V_H = 𝒍_t*S_t/(S*c_ma) or Horizontal Tail Volume Ratio = Horizontal Tail Moment Arm*Horizontal Tail Area/(Reference Area*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 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 & The Mean Aerodynamic Chord is a two-dimensional representation of the whole wing.

How to calculate Horizontal tail volume ratio?

Horizontal Tail Volume Ratio is a dimensionless parameter that characterizes the size and shape of an aircraft's horizontal tail surface, it is a crucial factor in determining the stability and control of an aircraft during flight, this ratio is calculated by dividing the product of the horizontal tail moment arm and area by the reference area and mean aerodynamic chord is calculated using Horizontal Tail Volume Ratio = Horizontal Tail Moment Arm*Horizontal Tail Area/(Reference Area*Mean Aerodynamic Chord). To calculate Horizontal tail volume ratio, you need Horizontal Tail Moment Arm (𝒍_t), Horizontal Tail Area (S_t), Reference Area (S) & Mean Aerodynamic Chord (c_ma). With our tool, you need to enter the respective value for Horizontal Tail Moment Arm, Horizontal Tail Area, Reference Area & Mean Aerodynamic Chord 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 Horizontal Tail Volume Ratio?

In this formula, Horizontal Tail Volume Ratio uses Horizontal Tail Moment Arm, Horizontal Tail Area, Reference Area & Mean Aerodynamic Chord. We can use 1 other way(s) to calculate the same, which is/are as follows -

Horizontal Tail Volume Ratio = -(Tail Pitching Moment Coefficient/(Tail Efficiency*Tail Lift Coefficient))

Home

FREE PDFs

🔍 Search