Lift due to Tail in Longitudinal Stability Formulas

Lift due to Tail refers to the aerodynamic force generated by the horizontal stabilizer of an aircraft. And is denoted by L_t. Lift due to Tail is usually measured using the Newton for Force. Note that the value of Lift due to Tail is always negative.

Formulas to find Lift due to Tail in Longitudinal Stability

fxTail Lift for given Tail Pitching MomentGo

fxLift due to Tail onlyGo

Longitudinal Stability formulas that make use of Lift due to Tail

fxPitching Moment due to TailGo

fxTotal Lift of Wing-Tail CombinationGo

fxLift due to Wing onlyGo

List of variables in Longitudinal Stability formulas

fx Pitching Moment due to Tail Go

fx Horizontal Tail Moment Arm Go

fx Lift Force Go

fx Lift due to Wing Go

FAQ

What is the Lift due to Tail?

Lift due to Tail refers to the aerodynamic force generated by the horizontal stabilizer of an aircraft. Lift due to Tail is usually measured using the Newton for Force. Note that the value of Lift due to Tail is always negative.

Can the Lift due to Tail be negative?

Yes, the Lift due to Tail, measured in Force can be negative.

What unit is used to measure Lift due to Tail?

Lift due to Tail is usually measured using the Newton[N] for Force. Exanewton[N], Meganewton[N], Kilonewton[N] are the few other units in which Lift due to Tail can be measured.

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