Effect of a Discontinuity on Turbulent Boundary-Layer-Thickness Parameters With Application to Shock-Induced Separation Page: 3 of 24
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_ Present analysis
--------Analysis of ref. 4Forward-facing step data
O Ref. 8 (9-In.-Supersonic Tunnelj
O Ref. 8 (Gas Dynamics Laborat.ory
o Ref. 9
VRef. 10
ARef. 11 (Blowdown facility)
bNRef. 12
S Mach number ratio,;
,
2 .Wedge data
S ARI Sweden (quoted in ref. 8)
>Ref. 12
'9Ref. 8 (Gas Dynamics Laboratory)
Mach number ratio,
0.703
Equation (4),
ref. 4
40. .81
Equation (8),
ref. 44 1
Mach number, M1(a) First peak pressure ratio for
forward-facing steps.(b) Inflection-point pressure ratios
obtained on wedges.Figure 3. - Pressure ratios associated with shock-induced, turbulent, boundary-
layer separation.0
-I I
I I I I --r - -
/
h
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Reshotko, Eli & Tucker, Maurice. Effect of a Discontinuity on Turbulent Boundary-Layer-Thickness Parameters With Application to Shock-Induced Separation, report, May 1955; (https://digital.library.unt.edu/ark:/67531/metadc57521/m1/3/: accessed April 24, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.