Inviscid parametric analysis of three-dimensional inlet performance

The advantages and design requirements of propulsion/airtranie integration for the high Mach number flight of air-breathing vehicles have led to extensive study of the three-dimensional sidevv all-compression scramjet inlet in recent years. Inlets of this genre afford a relatively simple, generic geometry while producing a highly complex, three-dimensional flowfield dominated by shock/shock and shock/boundary-layer interactions. While the importance of the viscous effects in high-speed inlet interactions is recognized, the present work addresses in a parametric fashion the inviscid effects of leading-edge sweep (between 0-70 deg) and inflow Mach number (between 2-12) on the inlet performance. Two-dimensional oblique shock theory is appropriately modified to account for the three-dimensional effects of leading-edge sweep and is applied throughout the inlet configuration to obtain inviscid shock impingement locations, mass capture, inlet compression, total pressure recovery, and kinetic energy efficiency. Comparison of these results with CFD indicates that the parametric trends are identified by this computationally quick and inexpensive method for preliminary design applications.

[1]  Jeffrey S. Hodge,et al.  Wind tunnel blockage study of a generic three-dimensional sidewall compression scramjet inlet at Mach 10 , 1991 .

[2]  Doyle Knight,et al.  Three-dimensional shock wave-turbulent boundary layer interactions generated by a sharp fin at Mach 4 , 1991 .

[3]  R. M. Williams,et al.  National Aero-Space Plane : Technology for America's Future , 1986 .

[4]  Ajay Kumar.  Numerical simulation of scramjet inlet flow fields , 1986 .

[5]  P. Batcho,et al.  Preliminary study of the interactions caused by crossing shock waves and a turbulent boundary layer , 1989 .

[7]  Charles R. Mcclinton,et al.  Numerical simulation of flow through the Langley parametric scramjet engine , 1989 .

[8]  K. Kudo,et al.  Mach 4 testing of scramjet inlet models , 1989 .

[9]  Scott D. Holland,et al.  Mach 6 testing of two generic three-dimensional sidewall compression scramjet inlets in tetrafluoromethane , 1990 .

[10]  Ajay Kumar,et al.  Numerical study of the effects of reverse sweep on scramjet inlet performance , 1992 .

[11]  B. Sekar,et al.  A numerical parametric study of a scramjet inlet in a Mach 6 arc heated test facility , 1990 .

[12]  Carl A. Trexler.  Inlet starting predictions for sidewall-compression scramjet inlets , 1988 .

[13]  Gary S. Settles,et al.  Swept shock/boundary-layer interactions - Tutorial and update , 1990 .

[14]  Frank K. Lu,et al.  Conical similarity of shock/boundary-layer interactions generated byswept and unswept fins , 1985 .

[15]  D. Knight,et al.  Crossing shock wave-turbulent boundary layer interactions , 1991 .

[16]  G. Y. Anderson,et al.  Survey of supersonic combustion ramjet research at Langley , 1986 .

[17]  Frank K. Lu,et al.  CONICAL SIMILARITY OF SHOCK/BOUNDARY LAYER INTERACTIONS GENERATED BY SWEPT FINS. , 1983 .

[18]  Ajay Kumar,et al.  Three-dimensional inviscid analysis of the scramjet inlet flow field , 1982 .

[19]  Goro Masuya,et al.  Mach 4 testing of scramjet inlet models , 1991 .