Peculiarities of the flows forming in processes of an impulse starting of a supersonic wind tunnel with different diffusers
- 2 Downloads
The peculiarities of supersonic unsteady flows forming in the processes of an impulse starting of a wind tunnel including a fore-chamber, a nozzle, a diffuser, and an exhaust tank are considered. The fore-chamber is separated from the flow duct by a thin breakable diaphragm. Before the wind tunnel starting, the gas contained in the exhaust tank is pumped out down to a very small pressure, and then the high-pressured working gas is fed into the fore-chamber. Upon reaching some value of this pressure, the diaphragm “instantaneously” ruptures, and the working gas starts exhausting through the nozzle: a rapid unsteady process of the wind tunnel starting arises. The numerical simulation of the flows forming at the impulse starting of the simplest experimental gas-dynamic facility has been carried out; the facility is arranged with a nozzle forming at its exit a two-dimensional supersonic flow with the Mach number of 2.9, and with replaceable diffusers having different relative areas of the throat. The numerical computations of two-dimensional unsteady flows have been carried out using the Reynolds-averaged Navier—Stokes equations and the SST k-ω turbulence model. The flow patterns computed numerically are compared with the data of the optical visualization of the flow obtained in the experimental gas-dynamic facility in the process of its starting.
Key wordssupersonic wind tunnel nozzle diffuser impulse starting process unsteady supersonic flow
Unable to display preview. Download preview PDF.
- 2.B.V. Boshenyatov, B.N. Gilyazetdinov, and V.V. Zatoloka, Experimental investigations of hypersonic inlets, in: Aeromechanics. Collection of Papers Devoted to the 60th Anniversary of V.V. Struminsky, Nauka, Moscow, 1976, P. 87–98.Google Scholar
- 3.R.J. McGregor, S. Molder, and T.W. Paisley, Hypersonic inlet flow starting in the Ryerson/University of Toronto gun tunnel, in: Investigations in the Fluid Dynamics of Scramjet Inlets, Ryerson Polytechnic University and the University of Toronto, Canada, 1992, P. 4.1–4.50.Google Scholar
- 4.D.M. van Wie, F.T. Kwok, and R.F. Walsh, Starting characteristics of supersonic inlets, in: 32nd AIAA, ASME, SAE, and ASEE Joint Propulsion Conference and Exhibit, July 1–3, 1996, Lake Buena Vista, FL., AIAA Paper, 1996, P. 96–2914.Google Scholar
- 5.A. Kantrowitz and C. Donaldson, Preliminary investigation of supersonic diffusers, NACA WRL-713, 1945.Google Scholar
- 8.X. Jiao, J. Chang, and D. Yu, Numerical study on hypersonic nozzle-inlet starting characteristics in a shock tunnel, Acta Astronautica J., 2017, P. 167–179.Google Scholar
- 10.V.I. Lashkov and A.A. Nikol’skii, Shock starting of a supersonic diffuser, Inzhenerhyi zhurnal, 1962, Vol. II, No. 1, P. 11–16.Google Scholar
- 12.B.D. Henshall, On Some Aspects of the Use of Shock Tubes in Aerodynamic Research, ARC Reports and Memoranda, No. 3044 (ARC Tech. Rep. 17407), London, 1957.Google Scholar
- 13.T.V. Bazhenova and L.G. Gvozdeva, Unsteady Interactions of Shock Waves, Nauka, Moscow, 1977.Google Scholar
- 14.The Riemann problem and discontinuous solutions: application to the shock tube problem, in I. Danaila, P. Joly, S. Kaber, and M. Postel (Eds.), An Introduction to Scientific Computing. Twelve Computational Projects Solved with MATLAB, 2007, P. 213–233.Google Scholar