some info. it should be understood that the use of differential thrust, on a model weighing more than one Ounce, is not recommended. Use PROPELLERS. this model should have a Dihedral main wing, and three channel control. throttle, rudder and elevator. correct design of a dihedral wing includes: two wing halves, and a fuselage-spanning, center-section, AND dihedral brace. five degrees of dihedral, per side, is enough. this model has a Tail-heavy distribution of mass; dom. if desired, the degree of tail-heaviness Could be reduced. MOVE the servos to a location NEAR the cg. (NOT aft of it). obviously, this mod will require the use of longer pushrods. READ MY LIPS. this is NOT a problem. this Assumes, of course, that longer pushrods are correctly designed/installed. the leading edges of a horiz-stab SHOULD be swept, a few degrees. material could be removed at the horiz- stab leading edges, accordingly. this mod Reduces Mass at the tail. this mod requires a reduction in the length of the root chords, of the tip-mounted vert-stabs. in order to complete this mod, the silhouette of the tip-mounted vert-stabs Should, then, be re-designed, accordingly. and more Mass is eliminated. improve/increase the (Inadequate) tapering of the tail boom. it should be understood that optimal tapering of the tail boom is NOT cosmetic. it is NOT opinion or a matter of choice. optimal tail boom taper is a Fundamental Part of the optimization of the dom of an airframe. it should be understood that, in the context of dom, the dorsal extension of the vert-stab on something like a cessna 172 is NOT part of the tail boom. at 7:23, it should be understood that the use of a more-outboard, motor location causes a reduction in the model's inherent, roll-axis stability. googletranslate dihedral wing; see turkey vulture silhouette reallybigyear.files.wordpress.com/2012/09/dihedrals.jpg see graphic; polyhedral (outboard dihedral) shown; so some degree, this configuration can be simpler/easier to brace, than where the joins in the wing are located inboard. mzqu.mit.edu/figs/3-W_VFA_Model.png
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some info. it should be understood that the use of differential thrust, on a model weighing more than one Ounce,
is not recommended. Use PROPELLERS. this model should have a Dihedral main wing, and three
channel control. throttle, rudder and elevator. correct design of a dihedral wing includes: two wing halves,
and a fuselage-spanning, center-section, AND dihedral brace. five degrees of dihedral, per side, is enough.
this model has a Tail-heavy distribution of mass; dom. if desired, the degree of tail-heaviness Could be reduced.
MOVE the servos to a location NEAR the cg. (NOT aft of it). obviously, this mod will require the use of
longer pushrods. READ MY LIPS. this is NOT a problem.
this Assumes, of course, that longer pushrods are correctly designed/installed.
the leading edges of a horiz-stab SHOULD be swept, a few degrees. material could be removed at the horiz-
stab leading edges, accordingly. this mod Reduces Mass at the tail. this mod requires a reduction in the length
of the root chords, of the tip-mounted vert-stabs. in order to complete this mod, the silhouette of the tip-mounted
vert-stabs Should, then, be re-designed, accordingly. and more Mass is eliminated.
improve/increase the (Inadequate) tapering of the tail boom. it should be understood that optimal tapering
of the tail boom is NOT cosmetic. it is NOT opinion or a matter of choice. optimal tail boom taper is a
Fundamental Part of the optimization of the dom of an airframe. it should be understood that, in the context of
dom, the dorsal extension of the vert-stab on something like a cessna 172 is NOT part of the tail boom.
at 7:23, it should be understood that the use of a more-outboard, motor location causes a reduction in the model's
inherent, roll-axis stability. googletranslate
dihedral wing; see turkey vulture silhouette
reallybigyear.files.wordpress.com/2012/09/dihedrals.jpg
see graphic; polyhedral (outboard dihedral) shown; so some degree, this configuration can be simpler/easier to brace,
than where the joins in the wing are located inboard.
mzqu.mit.edu/figs/3-W_VFA_Model.png