## DeltaWing:

Path: AerospaceUtils/ComponentModels

% Generates a single or double delta wing.
y is vertical, x is along the chord and z is along the span.
z1 is the spanwise location of the break in z2 is the spanwise
location of the wing tip. n is the number of z divisions. The
wing is an ellipsoidal front determined by lERatio. For a delta
wing make angle1 = angle2 and z1 = z2. Angles are from the span
vector. The taper fraction is the ratio of tip chord to
root chord. The wing thickness is always 1. The leading edge of the
root is at x = 0; the trailing edge is always at negative x.
Type DeltaWing for a demo.
--------------------------------------------------------------------------
Form:
[v, f] = DeltaWing( angle1, angle2, angleTE, z1, z2, xTE,
n, lERatio, taper, tRatio )
--------------------------------------------------------------------------
------
Inputs
------
angle1 (1,1) Angle of the first section (deg)
angle2 (1,1) Angle of the second section (deg)
angleTE (1,1) Trailing edge angle
z1 (1,1) Spanwise break of the first section
z2 (1,1) Wing tip
xTE (1,1) X of the trailing edge
n (1,1) Number of spanwise sections
lERatio (1,1) Leading edge x to y ratio
taper (1,1) Ratio of root to tip
tRatio (1,1) Ratio of thickness to chord at root
-------
Outputs
-------
v (:,3) Vertices
f (:,3) Faces
--------------------------------------------------------------------------

## Children:

Common: ComponentModels/Extrude
Math: Trigonometry/SinD
Math: Trigonometry/TanD

Back to the AerospaceUtils Module page