Download Numerical Simulation of Viscous Shock Layer Flows by Y.P. Golovachov PDF
By Y.P. Golovachov
The booklet is anxious with mathematical modelling of supersonic and hyper sonic flows approximately our bodies. everlasting curiosity during this subject is motivated, firstly, through aviation and aerospace engineering. The designing of airplane and house autos calls for a extra distinctive prediction of the aerodynamic and warmth move features. including broadening of the flight variety, this makes it essential to take note of a few gasoline dynamic and actual results brought on by rarefaction, viscous-inviscid interplay, separation, quite a few actual and chemical procedures brought on through fuel heating within the in depth bow surprise wave. The stream box round a physique relocating at supersonic pace may be divided into 3 components, particularly, surprise layer, close to wake together with base circulate, and much wake. The surprise layer move is bounded by means of the bow surprise wave and front and lat eral elements of the physique floor. a standard method of calculation of outrage layer flows is composed in a successive resolution of the inviscid fuel and boundary layer equations. while the afore-mentioned results turn into vital, implementation of those versions meets problems or perhaps turns into very unlikely. as a result, one has to take advantage of a extra basic technique in keeping with the viscous surprise layer concept.
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Extra resources for Numerical Simulation of Viscous Shock Layer Flows
Sample text
At the above parameters of the oncoming stream non-uniformity and sufficiently high Reynolds numbers, both sets provide the results demonstrating an existence of two vortices within the shock layer. The reduced equations predict a rise of the secondary vortex at smaller Reynolds numbers. 5 depict some calculation results. Here all distances are normalized by the sphere radius R, the pressure is normalized by Po V02 . The skin friction coefficient is defined as the ratio of the shear stress on the body surface to Po V02 • The subscript 0 denotes the gas parameters on the wake axis.
15 pertain to the air flow. 075, which may be explained by the viscosity increase due to the temperature jump on the body surface . With decreasing wall temperature, the temperature jump effect on the heat flux diminishes. 16 presents comparison of calculations of the heat transfer coefficient at the stagnation point of a sphere CH = qjPoo Voo (h* - hw) with experimental data by Gusev and Nikolskii (1971). One can see a good agreement between the calculation and experimental results. 0 -- .....
In calculation of both viscous and inviscid flows the bow shock shape may be distorted with the alternating sign error which is eliminated by the following smoothing procedure i = 0, 1, ... 25. The above numerical method reduces to solving the one-dimensional sets of equations. 5 and monotonicity in the regions of steep gradients provided that the local mesh Reynolds number Reh ;S 2 (Golovachov and Koleshko 1988). The latter restriction is removed in the modified method (Belousov et al 1991) in which the tangent velocity component and gas temperature variation across the shock layer are approximated with the exponential difference formulae following from the local fundamental solution of the model equation.