In advance of the ESWI RP measurement campaign in the European Transonic Wind Tunnel in 2014, numerical simulations for NASA's Common Research Model were performed using the DLR TAU code. The presented investigations are focused on the interaction between the separated flow of the main wing with the horizontal tail plane at high Mach numbers. This phenomenon, called transonic tail buffet, poses a serious risk and therefore limits the flight envelope for commercial aircraft.A mesh for the CRM was built including a high resolved tetrahedral block to reduce dissipative effects in the wake. A validation was conducted which shows excellent agreement to the results of the Drag Prediction Workshops. Based on lift polar simulations the buffet onset regime was defined and an inflow condition beyond this point was selected to perform an unsteady simulation. It is shown that a corner separation leads to a movement of the complex shock system on the upper surface of the main wing. Large vortices are shed which propagate downstream and massively influence the flow around the HTP followed by a high frequency response which is found in all integral coefficients.
Nomenclatureangle of the HTP [ • ] M Mach number [−] p pressure fluctuations [N/m 2 ] q ∞ dynamic pressure [N/m 2 ] Re Reynolds number [−] xyz cartesian coordinates [m] α angle of attack [ • ] η dimensionless span coordinate [−] ν t eddy viscosity [m 2 /s] Downloaded by CORNELL UNIVERSITY on July 30, 2015 | http://arc.aiaa.org |
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