Calculation by Solving of the Navier-Stokes Equations
for the Flow Downstream of an Afterbody with Thermal Effects
Isothermal Contours.
Research is actively conducted on base flows, which have practical importance for aircraft, missiles, launchers and projectiles. The problem of predicting the drag due to negative pressure created at the base and thermal effects on the afterbody of a propelled missile has not yet been solved satisfactorily due to the complexity of the flows in this region.
In this area, the modelling effort is being continued to obtain a better representation of the turbulence in the base regions and improve accounting of the aerothermochemical factors resulting from existence of a hot jet exhaust consisting of species that are still reacting. One of the objectives is also to improve prediction of the jet in the region near the afterbody to contribute to a more detailed characterisation of the infrared signatures.
Projectile designers are also interested in decreasing base drag by low-velocity fluid injection (base bleed) in the dead water. The activity in this area will be focussed on improving multicomponent type prediction methods which were the subject of major developments in the past and adapting them to various afterbody shapes.
