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YASim: Difference between revisions
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Clarified wing length and sweep values.
(Adding link to YSIMI visualization tool.) |
m (Clarified wing length and sweep values.) |
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This defines the main wing of the aircraft. You can have only one (but see below about using vstab objects for extra lifting surfaces). The wing should have a <stall> subelement to indicate stall behavior, control surface subelements (flap0, flap1, spoiler, slat) to indicate what and where the control surfaces are, and <control> subelements to map user input properties to the control surfaces. | This defines the main wing of the aircraft. You can have only one (but see below about using vstab objects for extra lifting surfaces). The wing should have a <stall> subelement to indicate stall behavior, control surface subelements (flap0, flap1, spoiler, slat) to indicate what and where the control surfaces are, and <control> subelements to map user input properties to the control surfaces. | ||
* '''x,y,z:''' The "base" of the wing, specified as the location of the mid-chord (not leading edge, trailing edge, or aerodynamic center) point at the root of the LEFT (!) wing. | * '''x,y,z:''' The "base" of the wing, specified as the location of the mid-chord (not leading edge, trailing edge, or aerodynamic center) point at the root of the LEFT (!) wing. | ||
* '''length:''' The length from the base of the wing to the midchord point at the tip. Note that this is not the same thing as span. | * '''length:''' The length from the midchord point of the base of the wing to the midchord point at the tip. Note that this is not the same thing as span. | ||
* '''chord:''' The chord of the wing at its base, along the X axis (not normal to the leading edge, as it is sometimes defined). | * '''chord:''' The chord of the wing at its base, along the X axis (not normal to the leading edge, as it is sometimes defined). | ||
* '''incidence:''' The incidence angle at the wing root, in degrees. Zero is level with the fuselage (as in an aerobatic plane), positive means that the leading edge is higher than the trailing edge (as in a trainer). | * '''incidence:''' The incidence angle at the wing root, in degrees. Zero is level with the fuselage (as in an aerobatic plane), positive means that the leading edge is higher than the trailing edge (as in a trainer). | ||
* '''twist:''' The difference between the incidence angle at the wing root and the incidence angle at the wing tip. Typically, this is a negative number so that the wing tips have a lower angle of attack and stall after the wing root (washout). | * '''twist:''' The difference between the incidence angle at the wing root and the incidence angle at the wing tip. Typically, this is a negative number so that the wing tips have a lower angle of attack and stall after the wing root (washout). | ||
* '''taper:''' The taper fraction, expressed as the tip chord divided by the root chord. A taper of one is a hershey bar wing, and zero would be a wing ending at a point. Defaults to one. | * '''taper:''' The taper fraction, expressed as the tip chord divided by the root chord. A taper of one is a hershey bar wing, and zero would be a wing ending at a point. Defaults to one. | ||
* '''sweep:''' The sweep angle of the wing, in degrees. Zero is no sweep, positive angles are swept back. Defaults to zero. | * '''sweep:''' The sweep angle of the wing, in degrees. Zero is no sweep, positive angles are swept back. Defaults to zero. [This looks to be the sweep of the mid-chord of the wing, not the sweep of the leading edge.] | ||
* '''dihedral:''' The dihedral angle of the wing. Positive angles are upward dihedral. Defaults to zero. | * '''dihedral:''' The dihedral angle of the wing. Positive angles are upward dihedral. Defaults to zero. | ||
* '''idrag:''' Multiplier for the "induced drag" generated by this surface. In general, low aspect wings will generate less induced drag per-AoA than high aspect (glider) wings. This value isn't constrained well by the solution process, and may require tuning to get throttle settings correct in high AoA (approach) situations. | * '''idrag:''' Multiplier for the "induced drag" generated by this surface. In general, low aspect wings will generate less induced drag per-AoA than high aspect (glider) wings. This value isn't constrained well by the solution process, and may require tuning to get throttle settings correct in high AoA (approach) situations. | ||