The flow inside the intake of a scramjet is found to be supersonic with Mach number of 2.5. From the instrumentations located inside the intake section, the static pressure and temperature were measured as 1 atm and 290 K, respectively. Inside the intake, the flow encounters the first compression ramp at an angle of 22º. As an intake engineer, investigatethe flow properties (Mach number, static pressure and temperature, stagnation pressure and temperature) after the resulting first oblique shock wave, so that the 2ndcompression ramp can be designed according to the requirements. Use the relevant tables and charts to assist your investigation. Commentif more shock waves are required to ensure that subsonic combustion is possible.
The flow inside the intake of a scramjet is found to be supersonic with Mach number of 2.5. From the instrumentations located inside the intake section, the static pressure and temperature were measured as 1 atm and 290 K, respectively. Inside the intake, the flow encounters the first compression ramp at an angle of 22º. As an intake engineer, investigatethe flow properties (Mach number, static pressure and temperature, stagnation pressure and temperature) after the resulting first oblique shock wave, so that the 2ndcompression ramp can be designed according to the requirements. Use the relevant tables and charts to assist your investigation. Commentif more shock waves are required to ensure that subsonic combustion is possible.
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