Abstract
Experimental study of flow around axisymmetric bodies in supersonic flow in case of a local injection into the boundary layer
Highlights
This paper presents the technique and results of experimental studies of supersonic flow around an axisymmetric (conical) model in the presence of symmetric and asymmetric gas injection into the boundary layer
Determination of aerodynamic characteristics of bodies in the range of Mach numbers M = (2 ÷ 5) is important for designing aircrafts of various purposes
This paper presents the technique and results of experimental studies of supersonic flow around an axisymmetric model in the presence of symmetric and asymmetric gas injection into the boundary layer
Summary
This paper presents the technique and results of experimental studies of supersonic flow around an axisymmetric (conical) model in the presence of symmetric and asymmetric gas injection into the boundary layer. The range of realized modes of operation of the installation: the Mach number M = (2 ÷ 7), the braking pressure at the nozzle exit section of the diffuser, forming the supersonic flow, P0 = (0.15 ÷ 0.3) MPa at static pressure P = (0.03 ÷ 0.07) MPa, the braking temperature of the incoming air flow T0 = (17.5 ÷ 250) °C.
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