000			01748aab a2200217 4500
008			240125b19901990|||mr||| |||| 00| 0 eng d
022			_a0017-9310
100			_aA. Palacio. _9880248
100			_aM.R. Malin. _9880249
100			_aN. Proumen. _9880250
100			_aL. Sanchez. _9880251
245			_aNumerical computations of steady transonic and supersonic flow fields
300			_a1193-1204 p.
520			_aA prediction procedure for computing the shock and expansion waves associated with transonic and supersonic flow is presented. In order to assess the capability of the model, calculations are carried out for a number of benchmark cases, for which analytical solutions or published data are available. The cases considered are: supersonic flow over jet vanes; transonic shocked flow in a nozzle; over- and under-expanded free jets with Mach disc formation; and supersonic flow in a cascade of wedges with shock reflection and Prandtl-Meyer expansion. The model, which includes the solution of the steady-state Euler equations as well as the full Navier-Stokes equations, utilizes some modifications made to an existing finite-volume formulation in order to ensure momentum and energy conservation through the shock waves. In all the cases, the calculations compare favourably with the analytical and experimental results.
650			_aNumerical Computations _9815529
650			_aSteady Transonic _9880252
650			_aSupersonic Flow Fields _9880253
773	0		_x00179310 _tInternational Journal of Heat and Mass Transfer _dNew York, U.S.A : Pergamon Subsidiary of Elsevier Science & Technology
856			_uhttps://www.sciencedirect.com/science/article/pii/001793109090251O
942			_2ddc _n0 _cART _o14993 _pMr. Muhammad Rafique Al Haj Rajab Ali (Late)
999			_c814803 _d814803