<DOC>
<DOCNO>
122
</DOCNO>
<TITLE>
a simplified approximate method for the calculation of the pressure
around conical bodies of arbitrary shape in supersonic and hypersonic
flow .
</TITLE>
<AUTHOR>
willi f. jacobs
</AUTHOR>
<BIBLIO>
lockheed aircraft corporation, georgia division
</BIBLIO>
<TEXT>
exact conical-flow solutions are available only for circular cones at
zero angle of attack .  for nonaxisymmetric cones or cones at angle of
attack, only approximate methods exist .  these methods are generally
quite complicated and further limited to certain body shapes or certain
mach-number ranges .  a great need was therefore felt for a simple
approximate method applicable to any arbitrarily shaped conical body at
zero incidence as well as at angle of attack .
such a method has been developed recently at lockheed and is presented
here in abbreviated form .  the method is based on the /equivalent-cone/
theory .  this theory determines the pressure on a conical body utilizing
information for a symmetric cone at zero angle of attack with the
same normal component of the free stream with respect to the surface as
the local element of the body considered .  this method works relatively
well at high mach numbers .  however, it is quite inconsistent at lower
mach numbers, especially for bodies which deviate considerably from
circular cones .  the equivalent-cone method does not give satisfactory
results, mainly due to the fact that it considers only the local surface
element on the body independent of the other body elements in the
newtonian-theory manner .
</TEXT>
</DOC>
