Accession Number : ADA269275

Title :   Investigations in the Fluid Dynamics of Scramjet Inlets.

Descriptive Note : Final rept.,

Corporate Author : TORONTO UNIV DOWNSVIEW (ONTARIO) INST FOR AEROSPACE STUDIES

Personal Author(s) : Molder, Sannu ; Sullivan, Philip A. ; McGregor, R. J. ; Sislian, J. P. ; Paisley, T. W.

Report Date : JUL 1992

Pagination or Media Count : 460

Abstract : Research on projects related to the hypersonic fluid mechanics of scramjet inlets is described. Four experimental tasks were performed which used a hypersonic gun tunnel to generate flows having stagnation enthalpies up to 1400K, Mach numbers of about 8.3, and Reynolds numbers for a typical model in the range of 5 to 15 million. The first project investigated the interaction of a shock wave with a laminar boundary layer in the neighborhood of a convex corner. The second project dealt with flow established in a two-dimensional inlet consisting of a forebody-cowl combination. The third project investigated flow in a circular duct having a length to diameter ratio of about 10. The fourth project detailed the effects on inlet performance of using three distinctly different inlet geometries: axisymmetric internal flow, two-dimensional internal flow, and axisymmetric external flow.... Inlets, Hypersonic technology, Liquid fuelled, Ramjet engines

Descriptors :   *RAMJET ENGINES, *SUPERSONIC COMBUSTION, *SUPERSONIC COMBUSTION RAMJET ENGINES, *HYPERSONIC FLOW, *RAMJET INLETS, CIRCULAR, DIAMETERS, DUCTS, FLUID MECHANICS, INLETS, INTERACTIONS, LAMINAR BOUNDARY LAYER, MACH NUMBER, MODELS, SHOCK WAVES, STAGNATION, TWO DIMENSIONAL, ENTHALPY, REYNOLDS NUMBER, ALUMINUM ALLOYS, BOUNDARY LAYER FLOW, STATIC PRESSURE, HEAT TRANSFER, HYPERSONIC WIND TUNNELS, FLOW SEPARATION, ACCELERATION.

Subject Categories : Jet and Gas Turbine Engines
      Aerodynamics

Distribution Statement : APPROVED FOR PUBLIC RELEASE