Abstract Every supersonic fan or compressor blade row has a streamtube, the “sonic streamtube,” which operates with relative inlet Mach number of one. A key parameter in design streamtube” is area ratio between throat and upstream passage area, Athroat/Ainlet. In this article, it shown that one unique value exists for ratio. If differs, even slightly, from value, then either chokes its suction ...

Designs for future aero engines aim increased efficiency with reduced exhaust gas and noise emissions. To achieve these goals, comprehensive physical understanding highly innovative solutions are necessary. Even though computational capabilities rising, the required confidence level is restrained. understand validate theoretical numerical models, extensive experiments at realistic operating con...

When powerful machines such as the Cray-2 became available in the late 1980s, a number of researchers investiWe investigate the use of an inexact Newton’s method to solve the potential equations in the transonic regime. As a test case, gated use of exact Newton’s method for solving steady we solve the two-dimensional steady transonic small disturbance state CFD problems. Direct sparse matrix so...

Flow control for turbulent skin-friction drag reduction is applied to a transonic airfoil improve its aerodynamic performance. The study based on direct numerical simulations (with up 1.8 billion cells) of the compressible flow around supercritical airfoil, at Reynolds and Mach numbers $Re_\infty = 3 \times 10^{5}$ $M_\infty =0.7$ . Control via spanwise forcing over fraction suction side airfoi...

In the following paper, the effects of a choked jet exhausted from the base of a non-lifting body on its total and base drags at sub-sonic and transonic regimes has been numerically investigated. Having surveyed the results of some turbulence models and after comparing with experimental results, an appropriate turbulence model i.e. SST K-?, has been chosen and this model has been used in the su...

We present preliminary results for the calculation of inviscid transonic flow over a complete aircraft. These results have been obtained by a novel approach that combines a new procedure for mesh generation with a new finite element method for solving the Euler equations. Introduction A principal goal of computational aerodynamics has been the calculation of transonic flow over a complete aircr...

The implementation of a 2D Euler solver on graphics hardware is described. The graphics processing unit is highly parallelised and uses a programming model that is well suited to flow computation. Results for a transonic turbine cascade test-case are presented. For large grids (10 nodes) a 40 times speed-up compared to a Fortran implementation on a contemporary CPU is observed.

The equations governing general relativistic, spherically symmetric, hydrodynamic accretion of polytropic fluid onto black holes are solved in Schwarzschild metric to investigate some of the transonic properties of the flow. Only stationary solutions are discussed. For such accretion, it has been shown that real physical sonic points may form even for flow with γ < 4

The mixed type problems arising in transonic flows in gas dynamics and isometric embeddings in geometry are considered. The two-dimensional steady Euler equations for the transonic flow past an obstacle such as an airfoil are first discussed. A viscous approximation to the steady transonic flow problem is presented, and its convergence is obtained by the method of compensated compactness. Then ...