Toward Supersonic Retropropulsion CFD Validation The CFD validation of hypersonic inlet configurations is explained. Glancing sidewall shock interaction is treated. Normal shock wave turbulent boundary layer interaction is discussed. Supersonic external compression inlets are introduced, and the computational fluid dynamics ( CFD) codes and tests needed to study flow associated with these inlets are outlined.
Topics covered include the philosophy of CFD validation, current validation efforts, the wing-body-tail Euler code, F-20 Euler simulated oil flow, and Euler Navier-Stokes code validation for 2D and 3D nozzle afterbody applications.ĬFD application to supersonic/hypersonic inlet airframe integration. Information is given in viewgraph form on the Computational Fluid Dynamics ( CFD) Workshop held July 14 - 16, 1987. Based on an evaluation criteria, recommendations for an initial CFD validation data base are given and gaps identified where future experiments would provide the needed validation data.ĬFD validation needs for advanced concepts at Northrop Corporation Building block and benchmark validation experiments are identified along with their test conditions and measurements. The elements of the roadmap are consistent with air-breathing vehicle design requirements and related to the important flow path components: forebody, inlet, combustor, and nozzle. A CFD validation roadmap for hypersonic flowsĪ roadmap for computational fluid dynamics ( CFD) code validation is developed.