<DOC>
<DOCNO>
682
</DOCNO>
<TITLE>
the lift of twisted and cambered wings in supersonic flow .
</TITLE>
<AUTHOR>
lance, g.n.
</AUTHOR>
<BIBLIO>
aero. quart. v. 6/2/, may, 1955 .
</BIBLIO>
<TEXT>
a generalised conical flow theory is used to deduce an integral equation
 relating the velocity potential on a delta wing/with subsonic leading
edges/to the given downwash distribution over the wing . the complete
solution of this integral equation is derived . this complete solution
is composed of two parts, one being symmetric and the other antisymmetric
with respect to the spanwise co-ordinate,. each part
represents a velocity potential . for example, if y is the spanwise
co-ordinate and x is measured in the free stream direction, then a
downwash of the form w-a ux/y/is symmetric and will give rise to a
symmetric potential, whereas w-a ux/y/sgn y is anti-symmetric and gives
rise to an anti-symmetric potential . the velocity potentials of such
flows are given in the form of tables for all downwashes up to and
including homogenous cubics in the spanwise and streamwise
co-ordinates . table iii gives similar formulae in the limiting case
were used over a cycle of the tumbling motion . the analytical expression
was in good agreement with numerical solutions of the complete nonlinear
equations of motion .
</TEXT>
</DOC>
