Boundary-Layer Instability Mechanisms on a Swept-Leading Edge at Mach 3.5 871858
Correlations for transition from laminar to turbulent flow on 45° and 60° swept cylinders based on data obtained in the NASA Langley Mach 3.5 Pilot Quiet Tunnel are presented. Variations of free-stream noise from high levels comparable to those in conventional wind tunnels to more than an order of magnitude lower had no effect on transition. However, when boundary-layer trips were attached to the leading edges, transition occurred at lower Reynolds numbers depending on both the trip height and the wind tunnel noise level.
Compressible linear stability calculations have been performed for the boundary layer on an infinite swept cylinder. The boundary layer on the attachment line has a generalized inflection point similar to that present in a flat-plate boundary layer. The results show that Tollmien-Schlichting waves are amplified in the attachment line boundary layer and that oblique waves have the highest growth rates. Wall cooling tends to be stabilizing. Calculations for the wavelengths of stationary cross-flow vortices that occur downstream of the attachment line are compared with experimental values.
Citation: Creel, T., Malik, M., and Beckwith, I., "Boundary-Layer Instability Mechanisms on a Swept-Leading Edge at Mach 3.5," SAE Technical Paper 871858, 1987, https://doi.org/10.4271/871858. Download Citation
Author(s):
T. R. Creel, M. R. Malik, I. E. Beckwith
Affiliated:
NASA Langley Research Center, Hampton, VA, High Technology Corp., Hampton, VA
Pages: 16
Event:
Aerospace Technology Conference and Exposition
ISSN:
0148-7191
e-ISSN:
2688-3627
Also in:
SAE 1987 Transactions: Aerospace-V96-6
Related Topics:
Engine cylinders
Wind tunnel tests
Noise
Turbulence
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