Plasma Control of Shock Wave Configuration in M=2 Inlet at Off-Design Mode

摘要

Particular objective of this work is to demonstrate the steering effect of weakly-ionized plasma on supersonic flow structure in a two-dimensional aerodynamic configuration with three-shock compression ramp at off-design operational mode. The model air inlet, designed for M=2 flow, was tested at M=2-3 and angle of attack AoA=0-8degr. Multi-electrode quasi-DC electrical discharge at power Wp=2-10kW was arranged upstream the compression surface. Significant plasma effect is considered on shocks configuration and flow parameters after the compression. CFD efforts manifest extra 3D information about particular details of flow parameters' modification due to plasma thermal impact. Such a technique can be posed as a feasible method for expanding of supersonic inlet's operational limits.