The objective of this research project is to carry out theoretical and numerical simulation of SR-71’s inlet for different Mach no. such as 1.7, 2.0, 2.5, 3.0 and 3.2. The SR-71’s inlet was having a variable spike geometry, which helps in sufficient airflow within the engine at supersonic speed and in pressure recovery.
Modelling and numerical analysis are being carried out in ANSYS-ICEM AND FLUENT. To validate the theoretical values/results, the computational analysis for the same Mach no, will be done.
The work is to be carried out to observe the changes across the shock in the inlet of SR-71. Additionally, stagnation pressure recovery calculation will also be done for the prescribed range of supersonic Mach no’s.
Modelling and numerical analysis are being carried out in ANSYS-ICEM AND FLUENT. To validate the theoretical values/results, the computational analysis for the same Mach no, will be done.
The work is to be carried out to observe the changes across the shock in the inlet of SR-71. Additionally, stagnation pressure recovery calculation will also be done for the prescribed range of supersonic Mach no’s.
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