In this work, a supersonic turbulent
ow over a long axisymmetric body was investigated,
both experimentally and computationally. The experimental study consisted of a series of wind tunnel tests
for the
ow over an ogive-cylinder body at a Mach number of 1.6 and at a Reynolds number of 8106, at
angles of attack between -2 and 6 degrees. It included the surface static pressure and the boundary layer
prole measurements. Further, the
ow around the model was visualized using a Schlieren technique. All
tests were conducted in the trisonic wind tunnel of the Qadr Research Center (QRC). Also, the same
ow
at zero angle of attack was computationally simulated using a multi-block grid (with patched method around
the block interfaces) to solve the thin layer Navier-Stokes (TLNS) equations. The numerical scheme used
was implicit Beam and Warming central dierencing, while a Baldwin-Lomax turbulence model was used
to close the Reynolds Averaged Navier-Stokes (RANS) equations. The static surface pressure results show
that the circumferential pressure at dierent nose sections varies signicantly with angle of attack (in
contrast to the circumferential pressure signatures along the cylindrical part of the body), while the total
pressure measurements in the boundary layer vary signicantly both radially and longitudinally. Two belts
with various leading edge angles were installed at dierent locations along the cylindrical portion of the
model. The computational results obtained were compared with some experimental ones (found by these
authors), showing considerably close agreements.