The distortion of a supersonic turbulent boundary layer by bulk compression and surface curvature

Mohan Jayaram, Alexander J. Smits

Research output: Contribution to conferencePaper

2 Scopus citations

Abstract

An experimental investigation of a supersonic turbulent boundary layer experiencing the effects of bulk compression and streamline curvature is described. The incoming boundary layer l.ad a Mach number of 2.87 and a unit Reynolds number of 6.3 × 107/m. Two different, constant-radius curved-wall models were used, one with δD/R = 0.10 (Model I) and one with δO/E = 0.02 (Model II). The total turning angle for botL cases was fixed at 8°. Dramatic increases in the turbulent normal and shear stresses were observed. The amplification of the normal stress was about the same in both models whereas the amplification of the shear stress was greater in Model I compared with Model II. The turbulence behavior for Model I was similar to that observed in the corresponding 8° compression corner flow, and the flow in the compression corner arid in Model I can be classed as “rapid” perturbations, in that the turbulence behavior appears to depend only on the total strain applied. The flow over Model II cannot be so easily classified and appears to be considerably more complex.

Original languageEnglish (US)
StatePublished - 1985
EventAlAA 23rd Aerospace Sciences Meeting, 1985 - Reno, United States
Duration: Jan 14 1985Jan 17 1985

Other

OtherAlAA 23rd Aerospace Sciences Meeting, 1985
CountryUnited States
CityReno
Period1/14/851/17/85

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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    Jayaram, M., & Smits, A. J. (1985). The distortion of a supersonic turbulent boundary layer by bulk compression and surface curvature. Paper presented at AlAA 23rd Aerospace Sciences Meeting, 1985, Reno, United States.