Accession Number : ADA265214


Title :   Calculations on Unsteady Type IV Interaction at Mach 8


Descriptive Note : Final rept. Dec 81-Aug 92,


Corporate Author : UNIVERSAL ENERGY SYSTEMS INC DAYTON OH


Personal Author(s) : Gaitonde, Datta


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a265214.pdf


Report Date : Jan 1993


Pagination or Media Count : 40


Abstract : The viscous unsteady flow due to a Type IV shock-on-shock interaction at Mach 8 is examined with an implicit flux-split scheme. A sequence of grids is utilized to perform a grid resolution study and the results are compared with experimental values. The formulation is finite-volume with higher order accuracy obtained with the MUSCL approach in conjunction with a limiter to prevent oscillations. Viscous terms are centrally differenced. The flow exhibits a limit cycle in aggregate quantities which can be related to the details for the flow structure. The supersonic jet bounded by the two shear layers displays large scale movement at a dominant frequency of 32 kHz. This is accompanied by variation in the angle between the terminating jet bow shock and the surface tangent. Unsteady separation regions are observed both above and below the point of jet impingement.... Hypersonic, High-speed, Type IV Interaction Flux- splitting, Upwinding, Implicit, Unsteady


Descriptors :   *UNSTEADY FLOW , *VISCOUS FLOW , *HYPERSONIC AIRCRAFT , FREQUENCY , ANGLES , LAYERS , HIGH VELOCITY , GRIDS , RESOLUTION , ACCURACY , SPLITTING , IMPINGEMENT , APPROACH , OSCILLATION , SURFACES , SHOCK , DIFFERENTIAL EQUATIONS , TANGENTS , SEPARATION , FLOW , BOW SHOCK


Subject Categories : Aerodynamics


Distribution Statement : APPROVED FOR PUBLIC RELEASE