A study of the vortex flow over 76/40-deg double-delta wing

A low-speed wind-tunnel study of the flow about a 76/40-deg double-delta wing is described for angles of attack ranging from -10 to 25 deg and Reynolds numbers ranging from 0.5 to 1.5 Million. The study was conducted to provide data for the purpose of understanding the vortical flow behavior and for validating Computational Fluid Dynamics methods. Flow visualization tests have provided insight into the effect of the angle of attack and Reynolds number of the vortex-dominated flow both on and off of the surface of the double-delta wing. Upper surface pressure recordings from pressure orifices and Pressure Sensitive Paint have provided data on the pressures induced by the vortices. Flowfield surveys were carried out at an angle of attack of 10 deg by using a thin 5-hole probe. Numerical solutions of the compressible thin-layer Navier-Stokes equations were conducted and compared to the experimental data

Loss of STOP Protein Impairs Peripheral Olfactory Neurogenesis

International audienceIn conclusion, STOP protein seems to be involved in the establishment of synapses in the olfactory glomerulus. Our results indicate that the olfactory system of STOP null mice is a well-suited experimental model (1) for the study of the mechanism of action of STOP protein in synaptic function/plasticity and (2) for pathophysiological studies of the mechanisms of altered neuronal connections in schizophrenia

Introduction and highlights

This chapter highlights the goals and achievements of NATO/RTO/AVT Task Group AVT-080: Leading-edge Vortex Breakdown over Slender Wings. After a survey and assessment of current experimental data in NATO and PfP countries, eight reliable experimental data sets have been collected and compiled. These data sets include time-average results at static model conditions, ensemble-average results at dynamic model conditions and unsteady results at static/dynamic model conditions. Ten state-of-the-art numerical solutions have been obtained on an ONERA 70\ub0 delta wing test caseusing different numerical methods, codes and grids For other wing configurations and test the effects of tunnel wall interference and of interactions between vortices are calculated. In addition to the experimental data and computational solutions, three advanced analytical solutions are included.Peer reviewed: YesNRC publication: Ye

Topology of the flow on a 65\ub0 delta wings

The flow topological structures over two 65\ub0 swept delta wings (a flat plate TUD wing and an IAR delta wing) have been investigated at varies angles of attack, sideslip and roll angles. The observed skin - friction line pattern has been used to infer the topology of the flow on the wing surface. Special attention was paid to the flow on the nose, the boundary-layer transition and the topological evolution as the attitude (control parameter) changes. Two large-scale wind tunnel models of the apex were constructed to obtain more data on the flow in this region. A correlative studies between kinematical flow space and critical states in dynamic space was conducted which shows useful information for further studies.Peer reviewed: YesNRC publication: Ye