Inlets of supersonic airplanes with deflection ramps
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Authors
Manjunath, Kallanna James
Issue Date
2020-05
Type
Electronic thesis
Thesis
Thesis
Language
ENG
Keywords
Aeronautical engineering
Alternative Title
Abstract
Results are presented for various values of freestream Mach numbers. For each Mach number, the two-ramp optimal configuration for maximum recovery ratio is found and resulted in a higher maximum total pressure recovery ratio then that of the one-ramp system. Then, for a certain configuration and Mach number, the supersonic inlet, as well as the control volume around it, are geometrically modeled in Siemens NX 12.0. A mesh is generated in the control volume using the meshing program within Ansys. Numerical simulations of a supersonic flow over a two-ramp inlet system are conducted using Ansys Fluent 2019 R1. The most updated simulation results are presented showing the starting state of the inlet. However, within the simulations conducted, the inlet flow stays in the starting condition as opposed to the operational condition. Any attempt to move the shock wave downstream to the throat did not work. Further studies should investigate establishing simulations of the inlet operational situation.
Description
May 2020
School of Engineering
School of Engineering
Full Citation
Publisher
Rensselaer Polytechnic Institute, Troy, NY