Abstract
A method for calculating the flowfield in propulsive nozzles is presented. The complete set of partial differentia] equations for time-dependent, compressible, viscous flow are solved using an efficient numerical procedure. The flowfield is subdivided into rectangular regions called cells and the fluxes of conserved properties (mass, momentum, and energy) into each cell are balanced using a finite-volume approach. Solid boundary conditions are enforced using an imaginary row of cells inside the body, while inflow and outflow boundary conditions are enforced using a method of characteristics formulation. The line Gauss-Seidel implicit technique of MacCormack is used to solve the Reynolds-averaged Navier-Stokes equations in the computational domain. The Baldwin-Lomax algebraic turbulence model is used. Multistream, axisymmetric nozzle flowfields, including mixing of the streams, can be analyzed using this method. A fan nozzle thrust reverser can be analyzed as well. Results are presented for a converging-diverging propulsive nozzle, multistream turbofan nozzles, and a turbofan nozzle with a thrust reverser. The computational results show excellent agreement with the experimental data. A two order of magnitude reduction in run cost relative to the MacCormack explicit method is demonstrated.
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