• Version
• 135 Downloads
• 3.73 MB File Size
• 1 File Count
• December 16, 2016 Create Date
• December 16, 2016 Last Updated

National Advisory Committee for Aeronautics, Technical Notes - Practical Calculation of Second Order Supersonic Flow Past Nonlifting Bodies of Revolution

Calculation of second-order supersonic flow past bodies of revolu—
tion at zero angle of attack is described in detail, and reduced to
routine computation. Use of an approximate tangency condition is shown
to increase the accuracy for bodies with corners. Tables of basic
functions and standard computing forms are presented. The procedure is
summarized so that one can apply it Without necessarily understanding
the details of the theory. A sample calculation is given, and several
examples are compared with solutions calculated by the method of
characteristics.

For predicting the pressure distribution over a nonlifting body of
revolution in supersonic flow, linearized theory is often found to be
inadequate. In the past, greater accuracy could be achieved only by
resorting to the laborious method of characteristics. Recently, however,
a second—order solution has been found which qi§h%2;it§'ggngegpfi;appIi:
cabilit yields greater accuracy than linearize heory, while requiring
cons rably less labor than the method of characteristics.

The present paper aims to give a complete description of the second—
order method, and to reduce it to routine computation. Previously
published descriptions of the procedure, which are inadequate in some
respects, are revised. Shortcuts in the computing scheme are pointed
out. Extensive tables of the required basic solutions are presented,
to be used in conjunction with standard computing forms. Several
examples illustrate the procedure.

The reader interested only in calculating the second-order solution
for a definite body, without necessarily understanding the details of
the theory, can turn directly to the final section Practical Use of
Method on page 26.