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  • 1
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    Large perturbation flow field analysis and simulation for supersonic inlets (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An analysis technique for simulation of supersonic mixed compression inlets with large flow field perturbations is presented. The approach is based upon a quasi-one-dimensional inviscid unsteady formulation which includes engineering models of unstart/restart, bleed, bypass, and geometry effects. Numerical solution of the governing time dependent equations of motion is accomplished through a shock capturing finite difference algorithm, of which five separate approaches are evaluated. Comparison with experimental supersonic wind tunnel data is presented to verify the present approach for a wide range of transient inlet flow conditions.
    Keywords: AERODYNAMICS
    Type: NASA-CR-174676 , NAS 1.26:174676
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Numerical Simulation For Supersonic Inlets (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Flows calculated for realistic engine-inlet conditions. Computer code LAPIN, large-perturbation inlet, developed to analyze large-perturbation, transient-flow fields in supersonic inlets. Robust, quick-running code capable of solving unsteady quasi-one-dimensional, inviscid-flow problems in mixed subsonic and supersonic regimes for inlets. Approach based upon quasi-one-dimensional, inviscid, unsteady formulation including engineering models of unstart/restart, bleed, bypass, and geometrical effects. Numerical solution of governing time-dependent equations of motion accomplished through shock-capturing, finite-difference algorithm. Program written in FORTRAN IV.
    Keywords: MECHANICS
    Type: LEW-14324 , NASA Tech Briefs (ISSN 0145-319X); 11; 10; P. 64
    Format: text
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    NASA TECHNICAL REPORTS
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