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Constant Velocity Combustion Scramjet Analysis, Lakshmi Srikanth Tiruveedula
Constant Velocity Combustion Scramjet Analysis, Lakshmi Srikanth Tiruveedula
Electronic Theses and Dissertations
The supersonic combustion ramjet or scramjet, is the most suitable engine cycle for sustained hypersonic flight in the atmosphere. The present work deals with the performance of a scramjet engine by parametrically analyzing the performance of the ideal scramjet using the engine parameters: specific thrust, fuel-to-air ratio, thrust specific fuel consumption, thermal efficiency, propulsive efficiency, overall efficiency and thrust flux. The objective of the work is to determine the desirable performance terms of the ideal scramjet, by varying three different candidate fuels and three different candidate materials for the combustion chamber. The engine parameters are related by the lower heating …
Parametric Scramjet Analysis, Jongseong Choi
Parametric Scramjet Analysis, Jongseong Choi
Electronic Theses and Dissertations
The performance of a hypersonic flight vehicle will depend on existing materials and fuels; this work presents the performance of the ideal scramjet engine for three different combustion chamber materials and three different candidate fuels. Engine performance is explored by parametric cycle analysis for the ideal scramjet as a function of material maximum service temperature and the lower heating value of jet engine fuels. The thermodynamic analysis is based on the Brayton cycle as similarly employed in describing the performance of the ramjet, turbojet, and fanjet ideal engines. The objective of this work is to explore material operating temperatures and …
Experimental Investigation Of Transonic Shock Oscillations On Naca 0018 At Incidence, Christopher Allen Farrell
Experimental Investigation Of Transonic Shock Oscillations On Naca 0018 At Incidence, Christopher Allen Farrell
Electronic Theses and Dissertations
A NACA 0018 airfoil model with a 3-inch chord was mounted into the trisonic wind tunnel at the National Center for Physical Acoustics at the University of Mississippi. Tunnel runs were conducted with the angle of incidence increasing from 0 degrees to 6 degrees at 1 degree increments, while the Mach number was held steady at 0.73. High-speed schlieren images were recorded at a sample rate of 4,000 Hz. A Matlab code was developed to display the spatial power spectral density distribution in the region of the shock. This code calculated the frequency spectrum at regular points along the range …