ORIGINAL: Mr Cox
The downthrust may reduce the ballooning but the engine and airfoil are fighting against each other so the increase in speed will not really match the extra power input.
A plane flying at full speed with a drooping tail much have an incidence problem on the stab? After all, the fuselage is just holding the wing and stab together, so if the angle of the fuselage is odd then there is something not right in the decalage I would think.
WRONG! The wing will fly at an angle-of-attack that it is forced into by the stab., if the pilot places the elevator in a position to do so. If the weight and airspeed are producing the proper lift for straight flight then lift equals gravity. A dragging tail will always be applying force against the wing to make it move somewhwere else.
Just go watch a jet airliner on final approach. The angle of the fuselage will be high, yet the airplane is on a descending path towards the runway, due to the high AOA (angle of attack) of the wing required for the relative slow speed. The elevator of the machine may appear to be inline with the stab, but that is because the stab, in most machines is a slab, and trims to an AOA that holds the wing in the high AOA. No big secret.
There again starts another great conversation. There is no such thing as "Stall Speed" a concept often used which does not exist.
Think about that one for a while. [sm=confused.gif]
L (lift) equals the Coeficient of lift (angle-of-attack) times 1/2 (air-mass density times Velocity squared times wing area). Hasn't failed yet in subsonic/transsonic convergent airflow.