Investigations of Supersonic Flow Around a Long Axisymmetric Body
نویسندگان
1 Department of Aerospace Engineering,Sharif University of Technology
2 Department of Aerospace Engineering,Sharif University of Technology
3 Department of Mechanical and Aeronautical Engineering,Sharif University of Technology
4 Department of Mechanical Engineering,Sharif University of Technology
doi
چکیده
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 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.
