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A comprehensive compilation of available turbulent flow separation data for overexpanded supersonic nozzles is presented with a discussion of correlation techniques, and prediction methods. Data are grouped by nozzle types: conical, contoured, and two dimensional wedge. Correlation of conical nozzle separation is found to be independent of nozzle divergence half-angle above the 9 deg, whereas the contoured nozzle data follow a different correlation curve. Zero pressure gradient prediction techniques are shown to predict adequately the higher divergence angle conical separation data, and an empirical equation is given for the contoured nozzle data correlation. Flow conditions for which the correlations are invalid are discussed and bounded. A nozzle boundary layer transition criterion is presented which can be used to show that much of the noncorrelating data in the literature are concerned with nonturbulent separation and which explains the previously reported external flow effects on nozzle separation.

Starting phenomena of two-dimensional hypersonic inlets with turbulent intake boundary layers at free stream Mach 6

Longitudinal aerodynamic characteristics of Viking lander spacecraft at hypersonic speed

Starting criterion for hypersonic inlets with large turbulent boundary layers, considering total pressure recovery from all shock and viscous losses

Hypersonic aerodynamic characteristics of delta wing x- 15 airplane configurations

Turbulent heat transfer associated with controls for attached or separated flow analyzed for design of hypersonic cruise aircraft

Flared afterbody aerodynamic characteristic predictions for aircraft stability at high Mach numbers, discussing turbulent separation

Aerodynamic characteristics of flared bodies noting geometry, Reynolds number and boundary layer state effects on stability

Base and afterbody pressures on boattailed bodies of revolution with hypersonic turbulent boundary layers

Center-line pressure distribution on two- dimensional bodies

Pressure distributions on flat plate delta wing swept 65 deg at hypersonic speeds at angles of attack from 65 deg to 115 deg and angles of roll from 0 deg to 25 deg at 90 deg angle of attack

For the interaction of shock waves with turbulent boundary layers, obtained experimental three-dimensional separation results and correlations with earlier two-dimensional and three-dimensional data are presented. It is shown that separation occurs much earlier for turbulent three-dimensional than for two-dimensional flow at hypersonic speeds.