<DOC>
<DOCNO>
758
</DOCNO>
<TITLE>
the lower bound of attainable sonic-boom over-pressure
and design methods of approaching this limit .
</TITLE>
<AUTHOR>
carlson,h.w.
</AUTHOR>
<BIBLIO>
nasa tn.d1494, 1962.
</BIBLIO>
<TEXT>
  from a study of existing sonic-boom
theory it has been possible to establish
an approximate lower bound of attainable
sonic-boom overpressure, which depends
only on the airplane length, weight, and
volume and on the flight conditions .
this lower bound may be approached over
a narrow range of flight conditions
through the application of appropriate
design considerations .  in general, for
intermediate values of lift coefficient
the major portion of the lift generating
surfaces must be located aft of the
maximum cross-sectional area, whereas for
higher values of lift coefficient
the maximum area must be well forward and or
the lift-producing surfaces must extend well toward the airplane nose .
</TEXT>
</DOC>
