لایه مرزی تراکم پذیر

Boundary layer flow compressibility, and permanently with sticky mass transfer (suction or injection flow) on an axial symmetric Bdnhhay study and numerical study is. Newton fluid gas (air) and considered a constant suction or injection flow rate as national or local by creating holes in different parts of the body surface is applied. General equations Navyr - Stokes equations with the approximate boundary layer, supersonic flow conversion and using Ghyrtshabhy Mhasbh distribution and integral to the heat transfer surface and nose profile to determine if the numerical boundary layer are analyzed. Governing equations with boundary conditions using the conversion Prabstn - Elliot coordinate the flow of lines and then transferred to the system and Exposure Nonlinear Equations with Parabolic the inclination toward nature as step by step solution Grdydhand To determine the flow profile, three-mode Dyvarh rigid, porous Dyvarh with suction or injection flow is considered. Numerical Flow Simulation on a promontory with a vertex angle of 20 degrees, Mach numbers in the 5 / 2, 5 / 3 and 5 / 4, and 35 kilo Pascal pressure 30, and 293 and 311 degree Kelvin temperatures has been done. In order to verify numerical simulation results with the numerical values of others and also the results of implementing software that Flvynt being compared are completely satisfactory.

The purpose of this investigation is consideration of aerothermodynamic phenomena over blunt and slender pointed bodies in hypersonic flows. Such results may be obtained by numerically solving the full Navier-Stokes equations or one of their various subsets، such as PNS equations. However، due to the excessive computer storage and CPU requirements، most people use their simple forms. In this work، a computer code was developed that uses an implicit finite difference method to solve non-similar، full compressible boundary layer equations for laminar، transitional، and turbulent flows over blunt and slender pointed bodies in hypersonic flows. Different test cases were studied and the related results were compared to benchmark CFD and experimental data showing relatively close agreements.