Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ 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

2 Other formulas that calculate the same Output

Tail area for given tail moment coefficient
Horizontal tail area=-Tail pitching moment coefficient*Reference Area*Mean aerodynamic chord/(Tail Efficiency*Horizontal tail moment arm*Tail Lift Coefficient) GO
Tail area for given tail efficiency
Horizontal tail area=Reference Area*(lift coefficient-Wing Lift Coefficient)/(Tail Lift Coefficient*Tail Efficiency) GO

Horizontal tail area for given tail volume ratio Formula

Horizontal tail area=Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail moment arm
S<sub>t</sub>=V<sub>H</sub>*S*c<sub>ma</sub>/𝒍<sub>t</sub>
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
Horizontal tail volume ratio 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
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

What is the most efficient wing shape?

The elliptical wing is aerodynamically most efficient because the elliptical spanwise lift distribution induces the lowest possible drag.

How to Calculate Horizontal tail area for given tail volume ratio?

Horizontal tail area for given tail volume ratio calculator uses Horizontal tail area=Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail moment arm to calculate the Horizontal tail area, The Horizontal tail area for given tail volume ratio is a function of the wing reference area, wing mean aerodynamic chord, tail volume ratio, and tail moment arm. Horizontal tail area and is denoted by St symbol.

How to calculate Horizontal tail area for given tail volume ratio using this online calculator? To use this online calculator for Horizontal tail area for given tail volume ratio, enter Horizontal Tail Volume Ratio (VH), Reference Area (S), Mean aerodynamic chord (cma) and Horizontal tail moment arm (𝒍t) and hit the calculate button. Here is how the Horizontal tail area for given tail volume ratio calculation can be explained with given input values -> 1.375 = 1.1*5*0.2/0.8.

FAQ

What is Horizontal tail area for given tail volume ratio?
The Horizontal tail area for given tail volume ratio is a function of the wing reference area, wing mean aerodynamic chord, tail volume ratio, and tail moment arm and is represented as St=VH*S*cma/𝒍t or Horizontal tail area=Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail moment arm. 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 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 and The horizontal tail moment arm is the distance between the lift center of the horizontal tail and the center of gravity of the aircraft.
How to calculate Horizontal tail area for given tail volume ratio?
The Horizontal tail area for given tail volume ratio is a function of the wing reference area, wing mean aerodynamic chord, tail volume ratio, and tail moment arm is calculated using Horizontal tail area=Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail moment arm. To calculate Horizontal tail area for given tail volume ratio, you need Horizontal Tail Volume Ratio (VH), Reference Area (S), Mean aerodynamic chord (cma) and Horizontal tail moment arm (𝒍t). With our tool, you need to enter the respective value for Horizontal Tail Volume Ratio, Reference Area, Mean aerodynamic chord and Horizontal tail moment arm 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 area?
In this formula, Horizontal tail area uses Horizontal Tail Volume Ratio, Reference Area, Mean aerodynamic chord and Horizontal tail moment arm. We can use 2 other way(s) to calculate the same, which is/are as follows -
  • Horizontal tail area=Reference Area*(lift coefficient-Wing Lift Coefficient)/(Tail Lift Coefficient*Tail Efficiency)
  • Horizontal tail area=-Tail pitching moment coefficient*Reference Area*Mean aerodynamic chord/(Tail Efficiency*Horizontal tail moment arm*Tail Lift Coefficient)
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