Reading the discussion about g limits on the RV (let's use an RV6 as the baseline).
Condition 1
Let's say the plane is loaded to it's aerobatic weight of 1390.
The airplane has a 180 lbs pilot and 16 gallons of fuel (all in the left tank)
Condition 2
Now the plane is loaded again to it's aerobatic weight of 1390.
The airplane has a 100 lbs pilot and 29.3 gallons of fuel (all in the left tank).
Even though the airplane is loaded to the same weight, does condition 2 (100 lbs pilot) put less bending moment on the wing spar than condition 1 (180 lbs pilot)?
Condition 1
Let's say the plane is loaded to it's aerobatic weight of 1390.
The airplane has a 180 lbs pilot and 16 gallons of fuel (all in the left tank)
Condition 2
Now the plane is loaded again to it's aerobatic weight of 1390.
The airplane has a 100 lbs pilot and 29.3 gallons of fuel (all in the left tank).
Even though the airplane is loaded to the same weight, does condition 2 (100 lbs pilot) put less bending moment on the wing spar than condition 1 (180 lbs pilot)?
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