Computational tools for supporting the testing of civil aircraft configurations in wind tunnels

Simulation of road vehicle natural environment in a climatic wind tunnel

Detailed experimental and accompanying numerical studies on the development of unsteady wakes past an aircraft under stall conditions are currently prepared by a consortium
of research institutions and universities. The experiments will be performed in the ETW cryogenic wind tunnel on the NASA Common Research Model. Besides wake surveys using
time-resolved cryo PIV measuring technique, wall interference measurements are planned. The tests scheduled for July 2013 are funded by the European Commission in the 7th framework program. In this paper results of preparatory CFD studies and wake analyses of the CRM model, the TR-PIV measuring technique and the ETW facility are presented along with the wind tunnel model and the planned test program.

Going for Experimental and Numerical Unsteady Wake Analyses Combined with Wall Interference Assessment by Using the NASA CRM Model in ETW

Conception of electronic wind tunnel and first results of its implementation

*† The design of a supersonic aerodynamic test section was implemented using computational modeling. Initial two-dimensional computational flow simulations revealed critical design issues such as starting the test section and model placement. These issues were resolved to provide a test section capable of operating throughout the Mach number range of the tunnel, with reduced flow blockage and substantial optical access. The final test section inlet design, tunnel starting data and optical access are shown.

S. Bosniakov

Papers

Experience in integrating CFD to the technology of testing models in wind tunnels