Abstract:
A fifth-order accurate compact difference scheme was used to compute the flow over an axisymmetric afterbody with jet exhaust. The solution was based on the mass-averaged Navier–Stokes equations combined with
a two-parameter differential model of turbulence. The computations were performed on a specially generated mesh such that the flow in the exterior and interior of the nozzle could be described simultaneously. Numerical results are presented for various external flow conditions and various chamber pressures.
This publication is cited in the following 2 articles:
A. D. Savel'ev, A. I. Tolstykh, D. A. Shirobokov, “Application of compact and multioperator schemes to the numerical simulation of acoustic fields generated by instability waves in supersonic jets”, Comput. Math. Math. Phys., 49:7 (2009), 1221–1234
Kuzenov V.V., “Matematicheskoe modelirovanie osnovnykh plazmodinamicheskikh kharakteristik v lazernom fakele vblizi alyuminievoi misheni”, Vestn. Mosk. gos. tekhnich. un-ta im. N. E. Baumana. Ser.: Mashinostroenie, 2009, no. 4, 45–77