ESDU 82018:2010

$126.75

The pressure distribution at zero incidence over selected families of blunt axisymmetric forebodies

Published By	Publication Date	Number of Pages
ESDU	2010-04-01	63

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Description

INTRODUCTION

This Item gives pressure distribution data for the flow of air*
over four families of blunt forebody at zero incidence;
ellipsoidal, spherically-curved nose with radiused shoulder,
spherically-blunted cone and spherically-blunted tangent ogive. The
families chosen (see Section 3) cover most of those likely to be
used in missile and re-entry body applications. Included among the
families are those considered in Item No. 68021 (Reference 21) and
Item No. 80021 (Reference 24) and as such the present Item acts as
a companion to those two.

The ranges of geometry and Mach number covered for each family
are as wide as possible dependent on the availability of data. The
pressure distribution data are presented (Section 4) in a direct
form as a ratio of the local static pressure to the stagnation
pressure at the nose of the forebody, while methods of estimating
the stagnation pressure itself are given in Section 5. The
abscissal parameter was selected as that being most appropriate to
the family under consideration. In this respect data for forebody
fineness ratios (l_f/Dof 0.5 or less
are presented against a dimensionless radial co-ordinate,
Y/R, which satisfactorily accommodates the case of the
flat face, while for forebody fineness ratios of 0.5 or more the
data are presented against an appropriate dimensionless axial
co-ordinate.

Section 6 provides a means of estimating, for inviscid flow, the
surface Mach number distribution and the temperature distribution
with no heat transfer from the corresponding pressure
distribution.

Section 7 considers the accuracy and applicability of the data,
which will typically be used in loading applications.

Section 8 lists the sources of data, both theoretical and
experimental, used to derive the data given while Table 10.1
provides a breakdown of the sources of data used for each pressure
distribution Figure.

Section 9 gives a worked example concerning a typical
application of the Item.

Appendix A summarises the geometrical relationships defining the
forebody shapes used in this Item. Also included are relationships
for surface length, which is sometimes used in experimental work,
for example in defining the pressure hole locations on test
bodies.

The data for the hemispherical head are used in Appendix B to
describe the flow development over a typical blunt body as the
free-stream Mach number traverses the full range from low subsonic
to high supersonic.

* Any formulae or theoretical methods used to generate data in
this Item requiring a value of the ratio of specific heat capacity
at constant pressure to the specific heat capacity at constant
volume used 1.4 for air.

Additional information