A method based on the theory of characteristics is presented for two-dimensional, supersonic nozzle design. Individual nozzle configurations for different applications are obtained by combining the geometric attributes of the symmetric, single expansion ramp, and Prandtl-Meyer type expansion nozzles. Corresponding to the design criteria, such as minimum length and optimum thrust efficiency, relations between desired properties of the flow field and nozzle geometry parameters are found, and a family of length-optimized, two-dimensional, supersonic nozzles is defined. The method can be applied for the design of wind tunnel and steam turbine nozzles as well as for thrust nozzle design of high Mach number aircraft.
2-D Supersonic Nozzle Design
1990
10 pages
Report
No indication
English
Rocket Engines & Motors , Aerodynamics , Spacecraft Trajectories & Flight Mechanics , Nozzle design , Supersonic nozzles , Two dimensional flow , Design analysis , Method of characteristics , Nozzle geometry , Prandtl-Meyer expansion , Flow distribution , Mach number , Steam turbines , Thrust , Wind tunnels , Foreign technology
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