A review of hypersonic boundary layer stability experiments in a quiet Mach 6 wind tunnel | Zendy

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A review of hypersonic boundary layer stability experiments in a quiet Mach 6 wind tunnel

Author(s) -

Stephen Wilkinson

Publication year - 1997

Publication title -

30th fluid dynamics conference

Language(s) - English

Resource type - Conference proceedings

DOI - 10.2514/6.1997-1819

Subject(s) - mach number , hypersonic speed , wind tunnel , hypersonic wind tunnel , quiet , boundary layer , aerospace engineering , mechanics , physics , engineering , astronomy

Three recent experimental studies of transition on cones with adverse pressure gradient produced by a flared afterbody and with the additive stability modifiers of wall cooling, angle of attack and bluntness are reviewed. All tests were conducted in a quiet Mach 6 wind tunnel. The dominant instability was found to be the second mode. For the cases examined with linear stability theory, the N factors at mode saturation were in the range of 8.5 to 11. Evidence of a combined second-mode/Gortler transition process was found. Mean, rms and spectral freestream data for the quiet facility is presented and the role of low frequency freestream noise is discussed.

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