Horizontal tail volume ratio Calculator

Category	Physics ↺
Physics	Flight Stability and Control ↺
Flight-Stability-And-Control	Static Stability and Control ↺
Static-Stability-And-Control	Contribution of Aircraft Components to Static Stability and Control ↺
Contribution-Of-Aircraft-Components-To-Static-Stability-And-Control	Tail Contribution (Contd.) ↺

✖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%
✖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]

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Vinay Mishra

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

Vinay Mishra has created this Calculator and 200+ more calculators!

Shikha Maurya

Indian Institute of Technology (IIT), Bombay

Shikha Maurya has verified this Calculator and 100+ more calculators!

< 11 Other formulas that you can solve using the same Inputs

Propeller Efficiency for given Endurance of Propeller-Driven Airplane

Propeller efficiency=Endurance of aircraft/((1/Specific Fuel Consumption)*((lift coefficient^1.5)/Drag Coefficient)*(sqrt(2*Freestream density*Reference Area))*(((1/Gross Weight)^(1/2))-((1/Weight without fuel)^(1/2)))) GO

Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane

Specific Fuel Consumption=(Propeller efficiency/Endurance of aircraft)*((lift coefficient^1.5)/Drag Coefficient)*(sqrt(2*Freestream density*Reference Area))*(((1/Gross Weight)^(1/2))-((1/Weight without fuel)^(1/2))) GO

Endurance of Propeller-Driven Airplane

Endurance of aircraft=(Propeller efficiency/Specific Fuel Consumption)*((lift coefficient^1.5)/Drag Coefficient)*(sqrt(2*Freestream density*Reference Area))*(((1/Gross Weight)^(1/2))-((1/Weight without fuel)^(1/2))) GO

Range of Jet Airplane

Range of aircraft=(sqrt(8/(Freestream density*Reference Area)))*(1/(Thrust-Specific Fuel Consumption*Drag Coefficient))*(sqrt(lift coefficient))*((sqrt(Gross Weight))-(sqrt(Weight without fuel))) GO

Minimum Thrust required for given weight

Thrust of an aircraft=(Dynamic Pressure*Reference Area*Zero-lift drag coefficient)+((Weight^2)/(Dynamic Pressure*Reference Area*pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO

Lift coefficient for given minimum required thrust

lift coefficient=sqrt(pi*Oswald efficiency factor*Aspect Ratio of a wing*((Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Zero-lift drag coefficient)) GO

Power required at sea-level condition

Power required at sea-level=sqrt(2*(Weight^3)*(Drag Coefficient^2)/([Std-Air-Density-Sea]*Reference Area*(lift coefficient^3))) GO

Zero-lift drag coefficient for given required thrust

Zero-lift drag coefficient=(Thrust of an aircraft/(Dynamic Pressure*Reference Area))-Coefficient of drag due to lift GO

Power required at an altitude

Power required at an altitude=sqrt(2*(Weight^3)*(Drag Coefficient^2)/(Density*Reference Area*(lift coefficient^3))) GO

Velocity at sea-level condition

Velocity at sea-level=sqrt(2*Weight/([Std-Air-Density-Sea]*Reference Area*lift coefficient)) GO

Velocity at an altitude

Velocity at an altitude=sqrt(2*Weight/(Density*Reference Area*lift coefficient)) GO

< 1 Other formulas that calculate the same Output

Horizontal tail volume ratio for given pitching moment coefficient

Horizontal Tail Volume Ratio=-Tail pitching moment coefficient/(Tail Efficiency*Tail Lift Coefficient) GO

Horizontal tail volume ratio Formula

Horizontal Tail Volume Ratio=Horizontal tail moment arm*Horizontal tail area/(Reference Area*Mean aerodynamic chord)
VH=𝒍t*St/(S*cma)

More formulas

Tail Pitching moment coefficient for given tail efficiency GO

Tail moment arm for given tail moment coefficient GO

Tail area for given tail moment coefficient GO

Tail lift coefficient for given pitching moment coefficient GO

Tail Efficiency for given pitching moment coefficient GO

Tail moment arm for given horizontal tail volume ratio GO

Wing Mean aerodynamic chord for given horizontal tail volume ratio GO

Wing Reference area for given horizontal tail volume ratio GO

Horizontal tail area for given tail volume ratio GO

Tail Pitching moment coefficient for given tail volume ratio GO

Horizontal tail volume ratio for given pitching moment coefficient GO

Tail Efficiency for given tail volume ratio GO

Tail lift coefficient for given tail volume ratio GO

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, The Horizontal tail volume ratio is a function of moment arm, tail area, wing reference area and wing mean aerodynamic chord. Horizontal Tail Volume Ratio and 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) and 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 -> 0.64 = 0.8*0.8/(5*0.2).

FAQ

What is Horizontal tail volume ratio?

The Horizontal tail volume ratio is a function of moment arm, tail area, wing reference area and wing 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 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 and The Mean aerodynamic chord is a two-dimensional representation of the whole wing.

How to calculate Horizontal tail volume ratio?

The Horizontal tail volume ratio is a function of moment arm, tail area, wing reference area and wing 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) and 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 and 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 and 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)

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