| Abstrakt: |
The problem of the laminar-turbulent transition control on flight vehicle elements has multiple application aspects: the friction drag reduction, modeling of natural flow conditions in wind tunnels, the elimination of the symmetric separated flow instability, the decrease of heat fluxes in hypersonic flows and others problems. W. Pffeninger indicated the possible improvement of the total flow structure due to the boundary layer laminarization. In some cases the laminar-turbulent location change can influence negatively on the total flow structure. In present report, different examples showing the importance of the transition mechanisms analysis and the analysis of all control consequences for different flow types from subsonic to hypersonic velocities. [ABSTRACT FROM AUTHOR] |
