<DOC>
<DOCNO>
1105
</DOCNO>
<TITLE>
numerical solutions for supersonic flow of an ideal
gas around blunt two-dimensional bodies .
</TITLE>
<AUTHOR>
fuller,f.b.
</AUTHOR>
<BIBLIO>
nasa tn.d791, 1961.
</BIBLIO>
<TEXT>
  the method described is an inverse one,. the shock shape is chosen
and the solution proceeds downstream to a body .  bodies blunter than
circular cylinders are readily accessible, and any adiabatic index can
be chosen .  the lower limit to the free-stream mach number available in
any case is determined by the extent of the subsonic field, which in
turn depends upon the body shape .  some discussion of the stability of
the numerical processes is given .  a set of solutions for flows about
circular cylinders at several mach numbers and several values of the
adiabatic index is included .
</TEXT>
</DOC>
