An experimental study of flow over flat and axisymmetric bodies

Abstract

Abstract.The technique and results of an experimental study of the flow structure and critical parameters of the flow over flat and axisymmetric bodies in a range of the Mach numbers (M = 2 ÷ 5) are presented.

An experimental study of flow over flat and axisymmetric bodies

“…The results of the drainage tests of the flow around a wedge and a cone in the range of the Mach numbers M = (2 ÷ 5) are shown in Fig.6, the pitch angle is equal to zero [2]. Analysis of the results obtained showed the difference in values of the static pressure upon the wedge and cone surfaces.…”

“…The noted effect is explained by the fact that the flow over a cone in the considered speed range has a spatial nature. It promotes smooth change in direction of the gas flow in comparison with the flow over a wedge [2,3]. At the same time it should be noted that the difference in values of the static pressure the flow over flat and axisymmetric models decreases with increasing the Mach number of the incoming flow.…”

“…On the basis of the presented technique an experimental study of critical parameters and the flow structure for symmetric models was conducted. The models are made in the form of a cone (axial symmetry) and a wedge (plane symmetry) [2] with diversion channels for pressure measurement upon surfaces. The corner of semi-solution made is 15 º. Drainage slots of diversion channels were carried out in the characteristic fixed points on a surface in the vertical plane.…”

Experimental study of flow around axisymmetric bodies in supersonic flow in case of a local injection into the boundary layer

“…The results of experiments when flow around the cone without gas injection in the range of Mach numbers [2] were used as a control-test in experimental studies. The comparison of flow structure when flow around cone with symmetric gas injection and without it showed qualitative change of interaction of supersonic air stream with the cone surface (formation of Mach cone).…”

“…Experimental researches were carried out on an aerodynamic installation [1,2]. 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, P 0 = (0.15 ÷ 0.3) MPa at static pressure P = (0.03 ÷ 0.07) MPa, the braking temperature of the incoming air flow T 0 = (17.5 ÷ 250) °C.…”