Abstract:

Preliminary researches are presented on numerical simulation of transonic wall interference for aircraft model tests.The wall effects on the tunnel flow field over the model and wall interference corrections to aerodynamic forces and moments are determined by using the solid wall conditions or measured pressure distributions near walls as the boundary conditions of test section and numerically calculating the tunnel flow field based on N S equations. Preliminary researches show that the method can effectively simulate the transonic tunnel flow over the model, and the corrected test results in 0.6m wind tunnel are in quite good agreement with the free interference reference data.

Key words: wallint erference, transonic flow, N-S equation, numerical simulation