philSweet
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I'm just catching up on the thread, so forgive the digression. A few pages back, Terry wrote
I would like to add four other observations to this list. Plane vs boat.
1. The drag of a plane's wing is a higher percentage of total drag (I think)
2. The location of the foil relative to the vessel's CG. A change in foil drag on a plane will not induce a huge pitch moment change like it will in a boat.
3. The location of the thrust vector relative to the vessel's CG. A change in thrust on a plane will not induce a huge pitch moment change in a plane like it will in a sailboat.
4. Relative span. In engineering terms, the relative size of the pitch, yaw and roll moments are very different.
Control of pitch, yaw and roll do not work in isolation. They each have a coupling effect on one another; and after a great deal of trial and error and study, an effective control system has evolved for planes that works with or in spite of these coupling effects. These coupling effects are highly dependent on moments of inertia; and for this reason I doubt that the eventual bifoiler control system will have much in common with that of a plane.
And one question (because you have to ask a Question
). Does anyone know what the relative drag values are (aero vs. hydro) as a function of speed. Kind of hard to solve force balance problems without this info. I figure aero is much higher than hydro at speed, but would drop sharply during a tack. The comments on relative foil loading at takeoff and at speed give some clues, but there's simply too much going on to use this to solve for aero drag.
Aircraft design practice has been quoted as a source of theory for foiler design. Foilers can certainly learn from aircraft design but the design of airfoil- and hydrofoil-supported craft is not exactly parallel. Here are some examples of differences:
1) Aircraft wings do not operate just below a medium discontinuity (the surface) like boat foils.
2) Boat foils do not have to operate during takeoff and landing just above a medium discontinuity (the ground) like aircraft wings.
3) An aircraft can lose far more height than a foiler without coming to grief.
4) A (foiled) sailor has a better chance of surviving a crash.
-so the same design guidelines may not apply to both aircraft and foiling boats.
I would like to add four other observations to this list. Plane vs boat.
1. The drag of a plane's wing is a higher percentage of total drag (I think)
2. The location of the foil relative to the vessel's CG. A change in foil drag on a plane will not induce a huge pitch moment change like it will in a boat.
3. The location of the thrust vector relative to the vessel's CG. A change in thrust on a plane will not induce a huge pitch moment change in a plane like it will in a sailboat.
4. Relative span. In engineering terms, the relative size of the pitch, yaw and roll moments are very different.
Control of pitch, yaw and roll do not work in isolation. They each have a coupling effect on one another; and after a great deal of trial and error and study, an effective control system has evolved for planes that works with or in spite of these coupling effects. These coupling effects are highly dependent on moments of inertia; and for this reason I doubt that the eventual bifoiler control system will have much in common with that of a plane.
And one question (because you have to ask a Question