Study of the Pressure Rise Across Shock Waves Required to Separate Laminar and Turbulent Boundary Layers Page: 2 of 21
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TECH LIBRARY KAFBPS, NM
III1 111111!111 I111111
IN NACA RM L52C21 0143841
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
STUDY OF THE PRESSURE RISE ACROSS SHOCK WAVES REQUIRED
TO SEPARATE LAMINAR AND TURBULENT BOUNDARY LAYERS
By Coleman duP. Donaldson and Roy H. Lange
A dimensional study and an experimental investigation have been
made on the pressure rise across shock waves required to cause separa-
tion of the boundary layer on a flat plate. The interaction of shock
wave and boundary layer was investigated experimentally when the bound-
ary layer was caused to separate from the surface of a tube of large
diameter compared with the boundary-layer thickness, by means of a
collar mounted on the tube. The investigation was conducted in a
Langley blowdown jet at a Mach number of 3.03, for a Reynolds number
range from about 2 x 106 to 19 x 106.
The dimensional study, based on certain simplifying assumptions,
indicates that the critical pressure rise across a shock wave which
just causes separation of the boundary layer is proportional to the
skin friction: The available experimental data on flat plates indicate
that the critical pressure rise varies as the Reynolds number to the
- power for laminar boundary layers and as the Reynolds number to the
-1power for turbulent boundary layers; therefore, these results are
in agreement with the prediction of the dimensional study. The Mach
number effect on the critical pressure coefficient for turbulent bound-
ary layers appears to follow that which is predicted for the skin-friction
coefficient on a flat plate. The significance of the results obtained
is discussed relative to certain practical design problems, such as
Increasing interest has been shown in recent years concerning the
phenomena associated with the interaction of shock waves and boundary
layers. A comprehensive review of the present status of the problem
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Donaldson, Coleman duP. & Lange, Roy H. Study of the Pressure Rise Across Shock Waves Required to Separate Laminar and Turbulent Boundary Layers, report, May 5, 1952; (digital.library.unt.edu/ark:/67531/metadc59270/m1/2/: accessed November 15, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.