EFFECTS OF DISTRIBUTED ROUGHNESS HEIGHT ON AERODYNAMIC CHARACTERISTICS AND BOUNDARY-LAYER TRANSITION OF A WING-BODY-TAIL CONFIGURATION AT A MACH NUMBER OF 1.61

摘要

An investigation has been conducted in the Langley 4-by 4-foot supersonic pressure tunnel to determine the effects of three-dimensional roughness trips on the boundary-layer transition and the longitudinal aerodynamic characteristics of a wing-body-tail configuration at a Mach number of 1.6l. The tests were made throughout a range of free-stream Reynolds numbers per foot from about 0.6 million to 8.0 million with the model angle of attack adjusted to produce zero lift. Tests were made without boundary-layer trips and with trips of different rough ness heights. At three test Reynolds numbers, data were recorded throughout an angle-of-attack range from about -1° to 12° with several roughness sizes and without the trip.