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This is a separate strength testing (load testing) of the elevator of an airplane, how was the load determined? How did the engineers determine the maximum elevator load?

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  • $\begingroup$ Related: What is the average aerodynamic load on a control surface of a commuter-sized airplane? $\endgroup$
    – user14897
    Oct 3, 2018 at 16:55
  • $\begingroup$ Which of the 3 questions are we answering here? Basically, I'm going with "test to destruction", and when it fails the maximum load has been determined. $\endgroup$
    – CrossRoads
    Oct 3, 2018 at 17:56
  • $\begingroup$ @CrossRoads - Your proposed method would test how much a control surface can take, but not how much it will experience in-flight. $\endgroup$
    – user14897
    Oct 3, 2018 at 18:45
  • $\begingroup$ That wasn't the question tho of the 3 questions. That answer requires more info than is available to answer. That would have to come from the designer. How much is needed? Enough to provide full elevator authority when coming in engine out and be able to safely flare. $\endgroup$
    – CrossRoads
    Oct 3, 2018 at 19:30

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Elevator loads are the function of the design and flight envelope. Looks like a small plane, so look up for example CS-VA 391 (or the correct national code for your category) how to calculate the loads. Base air force distribution on the horizontal tail can usually be assumed to be triangular, and increment from control surface deflection need to be added, also usually approximated as a triangular distribution acting from the hinge line.

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The elevator must be able to withstand aero loads at $V_{NE}$ and maximum deflection, using a safety factor of 1.5 at least.

The aero load = the hinge moment $H_M$ is:

$$H_M = C_h \cdot ½ \rho {V_h}^2 \cdot S_s \cdot {\bar{c}}_s$$

with

  • $½ \rho {V_h}^2$ = dynamic pressure at the control surface
  • $S_s$ = control surface area
  • ${\bar{c}}_s$ = mean aerodynamic chord of the surface behind the hinge axis.
  • $C_h$ = factor depending on angle of attack and surface deflection. The figure below is depicts the coefficients for the Fokker 27. (From TU Delft D 26-1 by prof. Gerlach)

enter image description here

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  • $\begingroup$ Can you Please provide the reference for the graph and the equation you shared? $\endgroup$
    – Hrishikesh Bhosale
    Aug 4 at 11:51
  • $\begingroup$ Re "The elevator must be able to withstand aero loads at VNE and maximum deflection, using a safety factor of 1.5 at least." -- really? Why bother to design the elevator to withstand a condition that will inevitably fail the wing? $\endgroup$
    – quiet flyer
    Aug 24 at 20:15
  • $\begingroup$ The graph is from university lecture handouts, I don't have access to them right now and cannot look up the exact figure. The equation is in the lectures as well. $\endgroup$
    – Koyovis
    Aug 24 at 20:32
  • $\begingroup$ @quietflyer Really. Wing structural failures are one thing, preventing the elevator from failing while the pilot is attempting to recover from a full stall is another highly recommended structural feature. $\endgroup$
    – Koyovis
    Aug 24 at 20:33

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