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In reply to the discussion: William Seger - Epic Fail [View all]William Seger
(11,726 posts)10. Fraud!
Here's the entire section that you quote-mined from:
§25.337 Limit maneuvering load factors.
(a) Except where limited by maximum (static) lift coefficients, the airplane is assumed to be subjected to symmetrical maneuvers resulting in the limit maneuvering load factors prescribed in this section. Pitching velocities appropriate to the corresponding pull-up and steady turn maneuvers must be taken into account.
(b) The positive limit maneuvering load factor n for any speed up to Vn may not be less than 2.1+24,000/ (W +10,000) except that n may not be less than 2.5 and need not be greater than 3.8where W is the design maximum takeoff weight.
(c) The negative limit maneuvering load factor
(1) May not be less than −1.0 at speeds up to VC; and
(2) Must vary linearly with speed from the value at VC to zero at VD.
(d) Maneuvering load factors lower than those specified in this section may be used if the airplane has design features that make it impossible to exceed these values in flight.
(a) Except where limited by maximum (static) lift coefficients, the airplane is assumed to be subjected to symmetrical maneuvers resulting in the limit maneuvering load factors prescribed in this section. Pitching velocities appropriate to the corresponding pull-up and steady turn maneuvers must be taken into account.
(b) The positive limit maneuvering load factor n for any speed up to Vn may not be less than 2.1+24,000/ (W +10,000) except that n may not be less than 2.5 and need not be greater than 3.8where W is the design maximum takeoff weight.
(c) The negative limit maneuvering load factor
(1) May not be less than −1.0 at speeds up to VC; and
(2) Must vary linearly with speed from the value at VC to zero at VD.
(d) Maneuvering load factors lower than those specified in this section may be used if the airplane has design features that make it impossible to exceed these values in flight.
In the first place, not only did you take that quote out of context, but you don't even understand what it actually says. The title of that section is "Limit maneuvering load factors." That would be the numbers on the vertical axis of your irrelevant Vg diagrams, so (c)(2) is only referring to the negative g, bottom edge, of the maneuvering envelope. So it does not apply to ALL loads, and what (c)(1) and (2) actually say is that up to Vc, the plane must be designed to withstand -1g (i.e. downward), but at Vd the design limit load factor can be 0g (i.e. the equivalent of free-fall vertically, since 1g would be level flight). It certainly does NOT say that the dynamic loads caused by simply moving through air are 0, which would be absurd, nor does it refer to the factor of safety. You are misinterpreting that FAR, and you still don't comprehend that "loads" in the relevant FARs means ALL stressing forces on the structure, not just g loads.
You continue to demonstrate that you don't understand this stuff well enough to even discuss it intelligently, and you say I'm digging myself into a hole? Please proceed.

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Fringe pilot group fails to define Vd, uses googled journalist made up definition
superbeachnut
Jun 2014
#3
Flew a desk quote mining lie, mirrors the fake Vd definition quote mining failure
superbeachnut
Jun 2014
#16
attacking a person, does not make the data wrong - no matter what other topics the person got wrong
superbeachnut
Jun 2014
#22