NASCRIN analyzes two-dimensional flow fields in supersonic combustion ramjet (scramjet) inlets. Solves two-dimensional Euler or Navier-Strokes equations in conservative form by unsplit, explicit, two-step finitedifference method. More recent explicit/implicit, two-step scheme also incorporated for viscous flow analysis. Algebraic, two-layer eddy-viscosity model used for turbulent flow calculations.
Analysis of Scramjet Inlets
NASA Tech Briefs ; 9 , 3
1986-01-01
Miscellaneous
No indication
English
NTIS | 2010
|AIAA | 2001
|NTRS | 1987
|British Library Conference Proceedings | 1995
|British Library Online Contents | 1995
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