Experimental investigation of wakes behind two-dimensional slender bodies at Mach number six

• Main Author: Batt, Richard George
• Format: Others
• Published: 1967
• Online Access: https://thesis.library.caltech.edu/5163/1/Batt_rg_1967.pdf; Batt, Richard George (1967) Experimental investigation of wakes behind two-dimensional slender bodies at Mach number six. Dissertation (Ph.D.), California Institute of Technology. doi:10.7907/3WW3-B746. https://resolver.caltech.edu/CaltechETD:etd-12292005-132450 <https://resolver.caltech.edu/CaltechETD:etd-12292005-132450>

NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in .pdf document. An experimental investigation has been conducted to determine mean flow properties for both near and far wakes behind several two-dimensional slender bodies at M[...] = 6. Three adiabatic wall models consisting of a flat plate model and two 20 [degree] included angle wedge models (H = .15", H = .3") were tested. The effect of wall temperature on wake properties was examined by cooling the larger of these two wedge models with the internal flow of liquid nitrogen ([...] = .19). Free stream Reynolds numbers were varied from [...] to [...] for each of these four configurations. In the far wake, measurements of total temperature, as determined with hot wire probes, and Pitot and static pressures were used to derive all other mean flow properties. The effect of transition on these far wake data was determined. Near wake flows were laminar for all adiabatic wall tests and at least for the two lowest test Reynolds numbers of the cold wall wedge. Base region flow field mappings and shear layer profiles were obtained for the .3"H wedge model by combining Pitot pressure data with hot wire measurements of total temperature and mass flux. These results illustrated that for slender bodies with flat bases, the basic structure for laminar near wakes is appreciably more complex for hypersonic than for supersonic flow primarily because, in hypersonic flow, the corner expansion fan extends into the separated shear layers and base region shocks now become imbedded within the viscous portion of the shear layers.