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This study aims to understand the effects of variable nose cone geometry on the performance of a ramjet engine. The performance of a Ramjet engine is primarily measured by its critical factors, namely, the pressure recovery ratio and velocity variations. Specifically, the combustion performance and overall efficiency of a ramjet engine depend on the pressure recovery ratio. Design modifications are carried out by using the formulae from the literature and simulations are carried out initially to validate the results from the literature for the specified nose cone angle. Further, the nose cone angle is varied from 6° to 20° with increments of 2°, and its impact on the overall performance and efficiency of the Ramjet engine is analyzed. Variations of pressure recovery ratio along the cowl and ramp surface of the engine are plotted along with their contours to determine the most favorable nose cone angle. Considering the optimal nose cone angle, the concavities are also varied along the ramp of the engine's inlet for a range of 2 mm with increments of around 0.5mm in between them. The best pressure recovery ratio which benefits the working of the engine is understood. Graphs are plotted to compare the various results obtained between the pressure recovery ratio along the cowl and ramp surface for varying angles and concavities. The best pressure recovery attained concurs with literature for a nose cone angle of 11° while its combination with the concavity of 4.318 mm gives the optimum performance. [ABSTRACT FROM AUTHOR]

This study aims to understand the effects of variable nose cone geometry on the performance of a ramjet engine. The performance of a Ramjet engine is primarily measured by its critical factors, namely, the pressure recovery ratio and velocity variations. Specifically, the combustion performance and overall efficiency of a ramjet engine depend on the pressure recovery ratio. Design modifications are carried out by using the formulae from the literature and simulations are carried out initially to validate the results from the literature for the specified nose cone angle. Further, the nose cone angle is varied from 6° to 20° with increments of 2°, and its impact on the overall performance and efficiency of the Ramjet engine is analyzed. Variations of pressure recovery ratio along the cowl and ramp surface of the engine are plotted along with their contours to determine the most favorable nose cone angle. Considering the optimal nose cone angle, the concavities are also varied along the ramp of the engine's inlet for a range of 2 mm with increments of around 0.5mm in between them. The best pressure recovery ratio which benefits the working of the engine is understood. Graphs are plotted to compare the various results obtained between the pressure recovery ratio along the cowl and ramp surface for varying angles and concavities. The best pressure recovery attained concurs with literature for a nose cone angle of 11° while its combination with the concavity of 4.318 mm gives the optimum performance. [ABSTRACT FROM AUTHOR]