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
Maiarutselvan V has verified this Calculator and 200+ more calculators!

11 Other formulas that you can solve using the same Inputs

Velocity in an accelerated flight
Velocity=((Radius of Curvature/Mass)*(Lift force+(Thrust force*sin(Thrust angle))-(Mass*[g]*cos(Flight path angle))))^(1/2) GO
Centrifugal Force in an accelerated flight
Centrifugal force=Lift force+(Thrust force*sin(Thrust angle))-(Mass*[g]*cos(Flight path angle)) GO
Coefficient of rolling friction during ground roll
Coefficient of Rolling Friction=Rolling Resistance/(Weight-Lift force) GO
Resistance force during ground roll
Rolling Resistance=Coefficient of Rolling Friction*(Weight-Lift force) GO
Thrust angle for an unaccelerated flight for given lift
Thrust angle=asin((Weight-Lift force)/Thrust of an aircraft) GO
Weight of aircraft in level, unaccelerated flight
Weight=Lift force+(Thrust of an aircraft*sin(Thrust angle)) GO
Dynamic pressure based on coefficient of lift
Dynamic Pressure=Lift force/(lift coefficient*Area) GO
lift coefficient
lift coefficient=Lift force/(Dynamic Pressure*Area) GO
Drag force with angle of attack
Drag Force=Lift force/cot(Angle of attack) GO
Glide angle
Glide angle=atan(Drag Force/Lift force) GO
Drag for given glide angle
Drag Force=Lift force*tan(Glide angle) GO

1 Other formulas that calculate the same Output

Tail lift for given tail pitching moment
Lift due to tail=-Pitching moment due to tail/Horizontal tail moment arm GO

Lift due to tail only Formula

Lift due to tail=Lift force-Lift due to wing
L<sub>t</sub>=L-L<sub>w</sub>
More formulas
Angle of attack at the tail GO
Angle of attack of the wing GO
Angle of incidence of wing GO
Downwash angle GO
Angle of incidence of tail GO
Total Lift of wing-tail combination GO
Lift due to wing only GO
Total Lift Coefficient of wing-tail combination GO
Wing Lift Coefficient of wing-tail combination GO
Tail Lift Coefficient of wing-tail combination GO
Tail Efficiency for given lift coefficients GO
Tail area for given tail efficiency GO
Pitching moment due to tail GO
Tail lift for given tail pitching moment GO
Tail Pitching moment for given lift coefficient GO
Tail lift coefficient for given pitching moment GO
Tail Pitching moment coefficient GO
Tail Pitching moment for given moment coefficient GO
Mean aerodynamic chord for given tail pitching moment coefficient GO
Vertical tail moment arm for given yawing moment coefficient GO

What is cantilever wing?

A wing that uses no external struts or bracing is a cantilever wing. All support is obtained from the wing itself. The wing spars are built in such a way that they carry all the torsion and bending loads.

How to Calculate Lift due to tail only?

Lift due to tail only calculator uses Lift due to tail=Lift force-Lift due to wing to calculate the Lift due to tail, The Lift due to tail only is the difference between the total lift force due to wing-tail combination and the lift due to wing alone. Lift due to tail and is denoted by Lt symbol.

How to calculate Lift due to tail only using this online calculator? To use this online calculator for Lift due to tail only, enter Lift force (L) and Lift due to wing (Lw) and hit the calculate button. Here is how the Lift due to tail only calculation can be explained with given input values -> -8 = 10-18.

FAQ

What is Lift due to tail only?
The Lift due to tail only is the difference between the total lift force due to wing-tail combination and the lift due to wing alone and is represented as Lt=L-Lw or Lift due to tail=Lift force-Lift due to wing. The lift force, lifting force or simply lift is the sum of all the forces on a body that force it to move perpendicular to the direction of flow and Lift due to wing is the lift force acting on the wing (only) of an aircraft .
How to calculate Lift due to tail only?
The Lift due to tail only is the difference between the total lift force due to wing-tail combination and the lift due to wing alone is calculated using Lift due to tail=Lift force-Lift due to wing. To calculate Lift due to tail only, you need Lift force (L) and Lift due to wing (Lw). With our tool, you need to enter the respective value for Lift force and Lift due to wing 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 Lift due to tail?
In this formula, Lift due to tail uses Lift force and Lift due to wing. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Lift due to tail=-Pitching moment due to tail/Horizontal tail moment arm
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