Analysis of a Continuously Variable Inlet and Isolator Design with Experimental, Computational, and Theoretical Comparison

In the following investigation a novel continuously variable inlet and isolator design will be analyzed using experimental, computational, and theoretical approaches. This inlet and isolator design serves to expand operability limits and increase pressure recovery associated with airbreathing propulsion inlets. This is achieved with the application of a continuously deformable inner mold line (IML) surface. Both the theoretical model and provided experimental and computational results will serve to further analyze the effects of this variable panel deformation operation and characterize shock structure behavior. This isolator design is tested experimentally at Mach 3.8 using Schlieren imaging and pressure sensitive paints (PSP) and investigated computationally using a Spalart Allmaras Unsteady Reynolds Averaged Navier Stokes (URANS) solver in Eilmer. A quasi 1-D analysis will be adopted to form the basis of the theoretical portion of this analysis. This analysis will be focused on the internal flow within the isolator section containing the continuously deformable surface. This comparison will serve to investigate the effectiveness of these traditional theoretical approaches for evolving and complex inlet and isolator geometries.