Investigations of Supersonic Flow Around a Long Axisymmetric Body


1 Department of Aerospace Engineering,Sharif University of Technology

2 Department of Mechanical and Aeronautical Engineering,Sharif University of Technology

3 Department of Mechanical Engineering,Sharif University of Technology


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
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 di erencing, 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 di erent 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 di erent 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.