Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Maiarutselvan V
PSG College of Technology (PSGCT), Coimbatore
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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

Tail moment arm for given horizontal tail volume ratio
Horizontal tail moment arm=Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail area GO

Tail moment arm for given tail moment coefficient Formula

Horizontal tail moment arm=-Tail pitching moment coefficient*Reference Area*Mean aerodynamic chord/(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient)
𝒍<sub>t</sub>=-C<sub>m<sub>t</sub></sub>*S*c<sub>ma</sub>/(η*S<sub>t</sub>*C<sub>L<sub>t</sub></sub>)
More formulas
Tail Pitching moment coefficient for given tail efficiency 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
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

What is the purpose of a horizontal stabilizer on a plane?

At the rear of the fuselage of most aircraft, one finds a horizontal stabilizer and an elevator. The stabilizer is a fixed-wing section whose job is to provide stability for the aircraft, to keep it flying straight. The horizontal stabilizer prevents up-and-down or pitching, the motion of the aircraft nose.

How to Calculate Tail moment arm for given tail moment coefficient?

Tail moment arm for given tail moment coefficient calculator uses Horizontal tail moment arm=-Tail pitching moment coefficient*Reference Area*Mean aerodynamic chord/(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient) to calculate the Horizontal tail moment arm, The Tail moment arm for given tail moment coefficient is a function of tail pitching moment coefficient, wing reference area, wing mean aerodynamic chord, tail efficiency, tail area, and tail lift coefficient. Horizontal tail moment arm and is denoted by 𝒍t symbol.

How to calculate Tail moment arm for given tail moment coefficient using this online calculator? To use this online calculator for Tail moment arm for given tail moment coefficient, enter Tail pitching moment coefficient (Cmt), Reference Area (S), Mean aerodynamic chord (cma), Tail Efficiency (η), Horizontal tail area (St) and Tail Lift Coefficient (CLt) and hit the calculate button. Here is how the Tail moment arm for given tail moment coefficient calculation can be explained with given input values -> -4.704301 = -0.7*5*0.2/(0.93*0.8*0.2).

FAQ

What is Tail moment arm for given tail moment coefficient?
The Tail moment arm for given tail moment coefficient is a function of tail pitching moment coefficient, wing reference area, wing mean aerodynamic chord, tail efficiency, tail area, and tail lift coefficient and is represented as 𝒍t=-Cmt*S*cma/(η*St*CLt) or Horizontal tail moment arm=-Tail pitching moment coefficient*Reference Area*Mean aerodynamic chord/(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient). Tail pitching moment coefficient is the coefficient of pitching moment associated with 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, The Mean aerodynamic chord is a two-dimensional representation of the whole wing, Tail Efficiency is defined as the ratio of dynamic pressure associated with the tail to dynamic pressure associated with an aircraft's wing, The Horizontal tail area is the area of the horizontal tail of an aircraft and Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity. .
How to calculate Tail moment arm for given tail moment coefficient?
The Tail moment arm for given tail moment coefficient is a function of tail pitching moment coefficient, wing reference area, wing mean aerodynamic chord, tail efficiency, tail area, and tail lift coefficient is calculated using Horizontal tail moment arm=-Tail pitching moment coefficient*Reference Area*Mean aerodynamic chord/(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient). To calculate Tail moment arm for given tail moment coefficient, you need Tail pitching moment coefficient (Cmt), Reference Area (S), Mean aerodynamic chord (cma), Tail Efficiency (η), Horizontal tail area (St) and Tail Lift Coefficient (CLt). With our tool, you need to enter the respective value for Tail pitching moment coefficient, Reference Area, Mean aerodynamic chord, Tail Efficiency, Horizontal tail area and Tail Lift Coefficient 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 moment arm?
In this formula, Horizontal tail moment arm uses Tail pitching moment coefficient, Reference Area, Mean aerodynamic chord, Tail Efficiency, Horizontal tail area and Tail Lift Coefficient. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Horizontal tail moment arm=Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail area
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