<DOC>
<DOCNO>
808
</DOCNO>
<TITLE>
an investigation of some aspects of the sonic boom
by means of wind tunnel measurements of pressures about
several bodies at a mach number of 2. 01 .
</TITLE>
<AUTHOR>
carlson,h.w.
</AUTHOR>
<BIBLIO>
nasa tn.d161, 1959.
</BIBLIO>
<TEXT>
  an investigation of some aspects
of the sonic boom has been made
with the aid of wind-tunnel measurements
of the pressure distributions
about bodies of various shapes .  the
tests were made in the langley
at a mach number of 2.01 and
at a reynolds number per foot of 2.5 x 10 .
measurements of the pressure
field were made at orifices in the surface
of a boundary-layer bypass
plate .  the models which represented both
fuselage and wing types of
thickness distributions were small enough
to allow measurements as far
away as 8 body lengths or 64 chords .  the
results are compared with
estimates made using existing theory .
  to the first order, the boom-producing
pressure rise across the bow
shock is dependent on the longitudinal
development of body area and not
on local details .  nonaxisymmetrical shapes
may be replaced by equivalent
bodies of revolution to obtain satisfactory
theoretical estimates
of the far-field pressures .
</TEXT>
</DOC>
