Novogorodtsev E.V.
DOI Number XXX-YYY-ZZZ
Conference Number HiSST 2018_35801117
As a result of flow compression in shock waves, wall friction, eddy formations and other phenomena, the flow in the inlet duct of the supersonic air intake becomes nonstationary and dynamic distortion appears. The dynamic distortion is quantified by the value of the root-mean-square parameter of the total pressure pulsations intensity ε that is calculated in the control section of the inlet duct. (ε is pulsating component of the total distortion parameter W= ͞Δ͞σо+ ε, ͞Δ͞σо is the circumferential distortion parameter). Numerical simulation of unsteady flow was performed using isolated trapezoidal intake configuration equipped with a boundary layer control system on the compression ramp surface. Numerical simulation of steady state flow was presented in [1-4]. To resolve the physical peculiarities of nonstationary turbulent flow, the modern eddy resolving DES (implemented in ANSYS CFX solver) method was applied. For three-dimensional viscous compressible flow computational modeling the geometry and the far field were discretized by means of spatial structured multi-block mesh. The mesh was generated manually, using the ICEM CFD software. To evaluate DES method capability to predict parameter ε values, numerical results were compared with experimental data. CFD computation data were processed using standard experimental methodology adopted at TsAGI. It was established, that the parameter ε values, obtained with CFD computation in the inlet duct control section, coincide with the experimental data with a sufficiently high accuracy for all investigated operating conditions,