dc.contributor.author |
Marson, G. B. |
|
dc.date.accessioned |
2016-11-09T14:59:41Z |
|
dc.date.available |
2016-11-09T14:59:41Z |
|
dc.date.issued |
1954-05 |
|
dc.identifier.uri |
http://dspace.lib.cranfield.ac.uk/handle/1826/10965 |
|
dc.description.abstract |
The pressure drag coefficients of a particular family
of convex logarithmic projectile nose shapes in which the nose
angle is an important parameter have been calculated over a range
of supersonic Mach numbers using a rapid approximate method due
to Zienkiewicz.5
The optimum nose angle for minimum wave drag of these
profiles for each Mach number has been obtained. It is shown
that above N = 1.5„ approximately, the optimum shape is similar
to the hypersonic optimum profile and has the sane or- less wave
drag than this profile. However for values of M/F, where P
is the fineness ratio, below 0.5, both the hypersonic and the
logarithmic optimum profiles have a higher drag than the so-called
cubic profile (Ref, 9). |
en_UK |
dc.language.iso |
en |
en_UK |
dc.publisher |
College of Aeronautics |
en_UK |
dc.relation.ispartofseries |
CoA/N-10 |
en_UK |
dc.relation.ispartofseries |
10 |
en_UK |
dc.title |
The calculation of the wave drag of a family of low-drag axisymmetric nose shapes of fineness ratio 4.5 at zero incidence at supersonic speeds |
en_UK |
dc.type |
Report |
en_UK |