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A simple model is presented for the analysis of inviscid flow fields over slender bodies accompanied by high rates of surface mass transfer. This model assumes a thin, inviscid injectant layer, which is separated from the outer flow by a contact discontinuity. Inviscid boundary-layer equations are shown to be applicable within the injectant layer, and the pressure gradient is found by matching ...

The influence of the in-stream pylon and strut on the performance of scramjet combustor was experimentally and numerically investigated. The experiments were conducted with a direct-connect supersonic model combustor equipped with multiple cavities. The entrance parameter of combustor corresponds to scramjet flight Mach number 4.0 with a total temperature of 947 K. The research results show tha...

Detached Eddy Simulations are performed for unsteady three-dimensional supersonic turbulent flow over an open L/D = 5 cavity at free-stream Mach number of 1.19. Numerical results are obtained from the explicit solution and Shear-Stress-Transport based simulations using the 3 order Roe scheme. Computational results are presented for the unsteady vortex and shock structures. The acoustic response...

Turbulence analysis of flow inside a hydrocyclone is carried out using commercially available CFD software ANSYS-CFX (release 11.0). Commercial CFD software(s) and their turbulence models have come a long way in accurately predicting the flow inside a hydrocyclone, both at the mean as well as at the turbulence level. Previous studies have shown, the more accurate the turbulence prediction is, t...

Supersonic Biplane as an Innovative Supersonic Transport Sonic boom noise inhibits the popularization of supersonic aircraft. This study is undertaken to develop a solution to this problem based on supersonic biplane theory. The feasibility of a proposed supersonic biplane concept “MISORA” presented in Fig. 1 has been investigated experimentally as well as numerically. Figure 2 shows a near-fie...

Supersonic biplanes can achieve low-boom and low-drag supersonic flights. In the present study, aerodynamic analysis of a two-dimensional stagger Bussmann biplane (staggered upper element by 0.5c) at zero degrees angle attack with trailing edge flap was investigated help computational fluid dynamics (CFD) tools. Due to wave cancellation effect, Busemann delivers positive drag reduction design M...