Experimental Study of Transition in a Compressible Free Shear Layer

Abstract

well with numerical methods. The transition and laminar flow theories are then joined to design an experiment aimed at producing non-equilibrium flows in a supersonic wind-tunnel, and at detecting the transition zone in such a flow. Flow and transition measurements done in this layer show that the shear-layer transition Reynolds number, based on the layer thickness and the fast-side unit Reynolds number, agrees with the corresponding number found by the equilibrium transition theory within 25%. It is concluded that the asymptotic transition theory utilized gives reasonable estimates even close to the trailing edge. Accession For NTIS GRA&I DTIC TAB Unanneunced El Justification By. Distribution/ Availability Codes Avail and/or fs Special StCuRITY CLASSIFICATIOU OF '-tAGE(tthtn Dole Er,

High-Speed Flight Propulsion Systems

“…The depressed growth rate of the two-dimensional Kelvin-Helmholtz disturbances, discussed in the previous section, may well alter the environment in which the three-dimensional motions develop, which are vital for the large interfacial area generation (see also Refs. [88][89][90]. At higher convective Mach numbers, shocks can certainly be expected to play an important role in this process.…”

Observations of supersonic free shear layers

“…Exceptions, to our knowledge, are experiments done by Demetriades & Bower (1982), Sanderson & Steel (1970) This would provide a useful test of the intrinsic Mach number concept. In addition, we wanted to study the effects of a larger variation of the parameter p1/ p1 than that afforded by the typical jet experiment of a single gas and with all total temperatures at room values.…”